IL-2 Sturmovik Flugzeuginformationen - VVS

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IL-2 Sturmovik Flugzeuginformationen - VVS

Beitrag von I/JG27_Zimmi » Di 27 Dez 2016, 17:55

Originalbeitrag: https://forum.il2sturmovik.com/topic/25 ... erational/

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Indicated stall speed in flight configuration: 143..164 km/h
Indicated stall speed in takeoff/landing configuration: 142..163 km/h
Dive speed limit: 620 km/h
Maximum load factor: 12 G
Stall angle of attack in flight configuration: 17.6 °
Stall angle of attack in landing configuration: 15 °

Maximum true air speed at sea level, engine mode - Boosted: 448 km/h
Maximum true air speed at 1800 m, engine mode - Nominal: 460 km/h
Maximum true air speed at 4500 m, engine mode - Nominal: 490 km/h

Service ceiling: 10500 m
Climb rate at sea level: 16.7 m/s
Climb rate at 3000 m: 13.8 m/s
Climb rate at 6000 m: 8.8 m/s

Maximum performance turn at sea level: 19.0 s, at 230 km/h IAS.
Maximum performance turn at 3000 m: 25.3 s, at 230 km/h IAS.

Flight endurance at 3000 m: 0.9 h, at 350 km/h IAS.

Takeoff speed: 145..175 km/h
Glideslope speed: 185..195 km/h
Landing speed: 135..145 km/h
Landing angle: 15.3 °

Note 1: the data provided is for international standard atmosphere (ISA).
Note 2: flight performance ranges are given for possible aircraft mass ranges.
Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass.
Note 4: climb rates and turn times are given for Boosted power.

Engine:
Model: M-63
Maximum power in Boosted mode at sea level: 1100 HP
Maximum power in Nominal mode at sea level: 930 HP
Maximum power in Nominal mode at 1800 m: 1000 HP
Maximum power in Nominal mode at 4500 m: 900 HP

Engine modes:
Nominal (unlimited time): 2200 RPM, 915 mm Hg
Boosted power (up to 5 minutes): 2300 RPM, 1065 mm Hg

Oil rated temperature in engine output: 55..90 °C
Oil maximum temperature in engine output: 125 °C
Cylinder head rated temperature: 120..200 °C
Cylinder head maximum temperature: 205 °C

Supercharger gear shift altitude: 3000 m

Empty weight: 1501 kg
Minimum weight (no ammo, 10% fuel): 1633 kg
Standard weight: 1878 kg
Maximum takeoff weight: 2146 kg
Fuel load: 191 kg / 260 l
Useful load: 645 kg

Forward-firing armament:
2 x 7.62mm machine gun "ShKAS", 500 rounds, 1800 rounds per minute, synchronized
2 x 7.62mm machine gun "ShKAS", 900 rounds, 1800 rounds per minute, wing-mounted
2 x 20mm gun "SsVAK", 90 rounds, 800 rounds per minute, wing-mounted (modification)

Bombs:
2 x 50 kg general purpose bombs "FAB-50sv"
2 x 104 kg general purpose bombs "FAB-100M"

Rockets:
Up to 6 x 7 kg rockets "ROS-82", HE payload mass 2.52 kg

Length: 6.04 m
Wingspan: 9 m
Wing surface: 14.54 m^2

Combat debut: June 1941

Additional airplane configurations list:
ShVAK 20mm wing-mounted guns with 90 rounds per each instead of default ShKAS wing-mounted machineguns
Additional mass: 40 kg
Ammunition mass: 22 kg
Guns mass: 98 kg
Estimated speed loss: 3 km/h

2 x 50 kg General Purpose Bombs FAB-50sv / 2 x 104 kg General Purpose Bombs FAB-100M
FAB-50sv:
Additional mass: 120 kg
Ammo mass: 104 kg
Racks mass: 20 kg
Estimated speed loss before drop: 13 km/h
Estimated speed loss after drop: 7 km/h
FAB-100M:
Additional mass: 228 kg
Ammo mass: 208 kg
Racks mass: 20 kg
Estimated speed loss before drop: 18 km/h
Estimated speed loss after drop: 7 km/h

4 x 82mm High Explosive unguided rockets ROS-82
Additional mass: 40 kg
Ammunition mass: 28 kg
Racks mass: 12 kg
Estimated speed loss before launch: 10 km/h
Estimated speed loss after launch: 7 km/h

6 x 82mm High Explosive unguided rockets ROS-82
Additional mass: 60 kg
Ammunition mass: 42 kg
Racks mass: 18 kg
Estimated speed loss before launch: 15 km/h
Estimated speed loss after launch: 10 km/h

One-piece frontal canopy section for better visibility
Additional mass: 0 kg
Estimated speed loss: 0 km/h

Operation features:
- Engine has a boost mode. To set boost mode it is necessary to push the boost lever fully forward and increase the engine to 2300 RPM.
- Engine has a two-stage mechanical supercharger which should be manually shifted at 3000m altitude.
- Engine mixture control is automatic when the mixture lever is set to maximum. It is possible to manually lean the mixture by moving the mixture control to less than maximum. This also reduces fuel consumption during flight.
- Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM.
- Oil radiator shutter and air cooling intake shutters control is manual.
- Airplane has no flight-control trimmers. Airplane is equipped with bendable trim tabs that can be set pre-flight by ground personnel.
- Airplane has a manual system for landing flaps and gear, for this reason it is necessary to extend landing flaps and gear before final approach. Landing flaps can be extended to any angle up to 53°.
- Airplane has a tail wheel control mechanism which is linked to rudder pedals. Because of this, it is necessary to avoid of large rudder pedal inputs when moving at high speed on the ground.
- Airplane has independent left and right mechanical wheel brakes. To brake it is necessary to push upper part of the rudder pedal.
- Airplane has a hydrostatic fuel gauge which shows total fuel remaining only when manual sucker lever is pushed in. In game this happens by itself during horizontal flight by every 10 seconds.
- Cockpit has side-doors which should be closed before takeoff to prevent damage.
- When bombs are installed there is a salvo controller, it has two release modes: single drop or drop two in a salvo.
- When rockets are installed there is a salvo controller, it has three launch modes: single fire, fire two in a salvo or fire by four in a salvo.
- The gunsight has a sliding sun-filter. There is also a back-up folding mechanical sight which can be used if main sight is damaged.
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Re: IL-2 Sturmovik Flugzeuginformationen -VVS

Beitrag von I/JG27_Zimmi » Di 27 Dez 2016, 17:58

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Indicated stall speed in flight configuration: 159..175 km/h
Indicated stall speed in takeoff/landing configuration: 134..147 km/h
Dive speed limit: 750 km/h
Maximum load factor: 12.8 G
Stall angle of attack in flight configuration: 17.3 °
Stall angle of attack in landing configuration: 15.1 °

Maximum true air speed at sea level, engine mode - Boosted: 525 km/h
Maximum true air speed at sea level, engine mode - Nominal: 493 km/h
Maximum true air speed at 7600 m, engine mode - Nominal: 626 km/h

Service ceiling: 11800 m
Climb rate at sea level: 15.9 m/s
Climb rate at 3000 m: 14.0 m/s
Climb rate at 6000 m: 10.2 m/s

Maximum performance turn at sea level: 22.4 s, at 270 km/h IAS.
Maximum performance turn at 3000 m: 28.7 s, at 270 km/h IAS.

Flight endurance at 3000 m: 2.5 h, at 350 km/h IAS.

Takeoff speed: 180..200 km/h
Glideslope speed: 195..205 km/h
Landing speed: 135..145 km/h
Landing angle: 15 °

Note 1: the data provided is for international standard atmosphere (ISA).
Note 2: flight performance ranges are given for possible aircraft mass ranges.
Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass.
Note 4: climb rates and turn times are given for Boosted power.

Engine:
Model: AM-35a
Maximum power in Boosted mode at sea level: 1350 HP
Maximum power in Nominal mode at sea level: 1120 HP
Maximum power in Nominal mode at 6000 m: 1200 HP

Engine modes:
Nominal (unlimited time): 2050 RPM, 1040 mm Hg
Boosted power (up to 10 minutes): 2050 RPM, 1240 mm Hg

Water rated temperature in engine output: 80..110 °C
Water maximum temperature in engine output: 120 °C
Oil rated temperature in engine intake: 40..80 °C
Oil maximum temperature in engine intake: 85 °C
Oil rated temperature in engine output: 115 °C
Oil maximum temperature in engine output: 120 °C

Supercharger gear shift altitude: single gear

Empty weight: 2650 kg
Minimum weight (no ammo, 10% fuel): 2831 kg
Standard weight: 3244 kg
Maximum takeoff weight: 3476 kg
Fuel load: 352 kg / 480 l
Useful load: 826 kg

Forward-firing armament:
2 x 7.62mm machine gun "ShKAS", 750 rounds, 1800 rounds per minute, synchronized
12.7mm machine gun "UB", 300 rounds, 1000 rounds per minute, synchronized
2 x 12.7mm machine gun "UB", 145 rounds, 1000 rounds per minute, wing-mounted (modification)
2 x 12.7mm machine gun "UB", 350 rounds, 1000 rounds per minute, synchronized (modification)
2 x 20mm gun "SsVAK", 150 rounds, 800 rounds per minute, synchronized (modification)

Bombs:
2 x 50 kg general purpose bombs "FAB-50sv"
2 x 104 kg general purpose bombs "FAB-100M"

Rockets:
6 x 7 kg rockets "ROS-82", HE payload mass 2.52 kg

Length: 8.255 m
Wingspan: 10.2 m
Wing surface: 17.44 m^2

Combat debut: July 1941

Additional airplane configurations list:
BK 12.7mm machineguns in wing-mounted gun pods with 145 rounds per each
Additional mass: 155 kg
Ammunition mass: 54 kg
Guns mass: 101 kg
Estimated speed loss: 13 km/h

BS 12.7mm nose-mounted machineguns with 350 rounds per each instead of default ShKAS and BS nose-mounted machineguns
Additional mass: 34 kg
Ammunition mass: 131 kg
Guns mass: 62 kg
Estimated speed loss: 0 km/h

ShVAK 20mm nose-mounted guns with 150 rounds per each instead of default ShKAS and BS nose-mounted machineguns
Additional mass: 4 kg
Ammunition mass: 69 kg
Guns mass: 94 kg
Estimated speed loss: 0 km/h

2 x 50 kg General Purpose Bombs FAB-50sv / 2 x 104 kg General Purpose Bombs FAB-100M
FAB-50sv:
Additional mass: 120 kg
Ammunition mass: 104 kg
Racks mass: 20 kg
Estimated speed loss before drop: 20 km/h
Estimated speed loss after drop: 12 km/h
FAB-100M:
Additional mass: 228 kg
Ammunition mass: 208 kg
Racks mass: 20 kg
Estimated speed loss before drop: 27 km/h
Estimated speed loss after drop: 12 km/h

6 x 82mm High Explosive unguided rockets ROS-82
Additional mass: 60 kg
Ammunition mass: 42 kg
Racks mass: 18 kg
Estimated speed loss before launch: 23 km/h
Estimated speed loss after launch: 17 km/h

Operation features:
- Engine has a boost mode which is engaged by setting the mixture control lever to maximum.
- Engine has a single-stage mechanical supercharger which does not require manual control.
- Engine mixture control is automatic when the mixture lever is set to the intermediate (50%) position. It is possible to manually lean the mixture by setting the control to less than 50%. This will reduce fuel consumption during flight.
- Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM.
- Water and oil radiator shutter control is manual.
- Airplane has only the pitch and yaw flight-control trimmers.
- Airplane has automatic wing slats. They deploy when the high angle of attack increases which makes pre-stall softer.
- Landing flaps have a limiter for the maximum angle. The flaps have an extended range from 0° to 50°. The landing flaps have pneumatic actuator. Flaps can only be instantly extended to the angle which is set by limiter, gradual extending is impossible. Due to weak force of the actuator the extended landing flaps may retract upward by the airflow when the airspeed is more than 220 km/h. For this reason, it is necessary to remember that flaps will not extend fully in case of high speed. In case of a high-speed landing approach the flaps may extend a few steps right before landing.
- Airplane has a tailwheel control system which is unlocked and made controllable by the rudder if the rudder pedal is pressed more than for 40% of its range. The tailwheel remans locked if pedals are deflected less than 40%. Because of this, it is necessary to avoid large rudder pedal inputs when moving at high speed, or be ready to control the airplane with an unlocked tailwheel should large rudder inputs be made.
- Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other.
- Airplane has a fuel gauge which shows total fuel remaining.
- It is impossible to open or close the canopy at high speed due to strong airflow. The canopy has no emergency release, so bail out requires the speed drop before it.
- When bombs are installed a salvo controller can be used, it has two release modes: single drop or drop two in a salvo.
- When rockets are installed a salvo controller can be used, it has three launch modes: single fire, fire two in a salvo or fire four in a salvo.
OLt. Zimmermann
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Re: IL-2 Sturmovik Flugzeuginformationen - VVS

Beitrag von I/JG27_Zimmi » Di 27 Dez 2016, 17:59

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Indicated stall speed in flight configuration: 136..156 km/h
Indicated stall speed in takeoff/landing configuration: 128..146 km/h

Dive speed limit: 570 km/h
Maximum load factor: 11.5 G
Stall angle of attack in flight configuration: 19.4 °
Stall angle of attack in landing configuration: 17.5 °

Maximum true air speed at sea level, engine mode - Boosted: 430 km/h
Maximum true air speed at sea level, engine mode - Nominal (at 2150 RPM): 421 km/h
Maximum true air speed at 2500 m, engine mode - Nominal (at 2150 RPM): 455 km/h

Service ceiling: 7500 m
Climb rate at sea level: 9.4 m/s
Climb rate at 3000 m: 8.9 m/s
Climb rate at 6000 m: 3.9 m/s

Maximum performance turn at sea level: 23.1 s, at 250 km/h IAS.
Maximum performance turn at 3000 m: 32.6 s, at 250 km/h IAS.

Flight endurance at 3000 m: 1.7 h, at 300 km/h IAS.

Takeoff speed: 150..190 km/h
Glideslope speed: 185..195 km/h
Landing speed: 130..140 km/h
Landing angle: 11.7 °

Note 1: the data provided is for international standard atmosphere (ISA).
Note 2: flight performance ranges are given for possible aircraft mass ranges.
Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass.
Note 4: climb rates are given for Nominal power, turn times are given for Boosted power.

Engine:
Model: AM-38
Maximum power in Boosted mode at sea level: 1600 HP
Maximum power in Nominal mode at sea level: 1500 HP
Maximum power in Nominal mode at 1650 m: 1500 HP

Engine modes:
Nominal (unlimited time): 2050 RPM, 1180 mm Hg
Boosted power (up to 10 minutes): 2150 RPM, 1280 mm Hg

Water rated temperature in engine output: 80..110 °C
Water maximum temperature in engine output: 120 °C
Oil rated temperature in engine intake: 40..80 °C
Oil maximum temperature in engine intake: 85 °C
Oil rated temperature in engine output: 115 °C
Oil maximum temperature in engine output: 120 °C

Supercharger gear shift altitude: single gear

Empty weight: 4242 kg
Minimum weight (no ammo, 10% fuel): 4464 kg
Standard weight: 5049 kg
Maximum takeoff weight: 5888 kg
Fuel load: 470 kg / 641 l
Useful load: 1646 kg

Forward-firing armament:
2 x 20mm gun "SsVAK", 210 rounds, 800 rounds per minute, wing-mounted
2 x 7.62mm machine gun "ShKAS", 750 rounds, 1800 rounds per minute, wing-mounted
2 x 23mm gun "VYa-23", 150 rounds, 600 rounds per minute, wing-mounted (modification)

Bombs:
Up to 6 x 50 kg general purpose bombs "FAB-50sv"
Up to 6 x 104 kg general purpose bombs "FAB-100M"
2 x 254 kg general purpose bombs "FAB-250sv"

Rockets:
8 x 7 kg rockets "ROS-82", HE payload mass 2.5 kg
8 x 15 kg rockets "RBS-82", HEAT payload mass 7.2 kg
8 x 42 kg rockets "ROFS-132", HE payload mass 21.3 kg

Length: 11.5 m
Wingspan: 14.6 m
Wing surface: 38.5 m^2

Combat debut: June 1941

Additional airplane configurations list:

2 VYa-23 23mm wing-mounted guns with 150 rounds per each
Additional mass: 110 kg
Ammunition mass: 170 kg
Guns mass: 132 kg
Estimated speed loss: 1 km/h

6 x 50 kg General Purpose Bombs FAB-50sv / 6 x 104 kg General Purpose Bombs FAB-100M
FAB-50sv:
Additional mass: 300 kg
Ammunition mass: 300 kg
Estimated speed loss before drop: 5 km/h
Estimated speed loss after drop: 0 km/h
FAB-100M:
Additional mass: 624 kg
Ammunition mass: 624 kg
Estimated speed loss before drop: 9 km/h
Estimated speed loss after drop: 0 km/h

2 x 254 kg General Purpose Bombs FAB-250sv
Additional mass: 538 kg
Ammunition mass: 508 kg
Racks mass: 30 kg
Estimated speed loss before drop: 19 km/h
Estimated speed loss after drop: 9 km/h

8 x 82mm Armour Piercing unguided rockets RBS-82
Additional mass: 144 kg
Ammunition mass: 120 kg
Racks mass: 24 kg
Estimated speed loss before launch: 13 km/h
Estimated speed loss after launch: 8 km/h

8 x 132mm High Explosive unguided rockets ROFS-132
Additional mass: 376 kg
Ammunition mass: 336 kg
Racks mass: 40 kg
Estimated speed loss before launch: 20 km/h
Estimated speed loss after launch: 12 km/h

Operation features:
- Engine has a boost mode which is engaging by setting mixture control lever to maximum position.
- Engine has a single stage mechanical supercharger which does not require manual control.
- Engine mixture control is automatic when the mixture lever is set to the intermediate (50%) position. It is possible to manually lean the mixture by moving the control lever to less than 50%. This will lower fuel consumption during flight.
- Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM.
- Water and oil radiator shutter control is manual. Airplane has armored oil radiator shutters which should to be closed on start of ground attack to reduce possibility of combat damage. After finishing the attack, it is necessary to re-open the shutters to the required position.
- Airplane has only the pitch flight-control trimmer.
- Landing flaps have a pneumatic actuator. Flaps can only be fully extended; gradual extending is impossible. Due to the weak force of the actuator the extended landing flaps may be pressed upwards by the airflow if the airspeed is more than 220 km/h. Remember that the flaps will not extend fully in case of high speed. In case of a high-speed landing approach the flaps may extend a few steps further right before landing.
- Airplane has a manual tail wheel lock. Wheel should be locked when taxiing straight for a long distance and before takeoff and landing.
- Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other.
- Airplane has a fuel gauge which shows the amount of remaining fuel in the front or bottom fuel tank depending on the switch position. In game the fuel indication switch changes by itself during horizontal flight by every 10 seconds. Rear fuel tank level is not indicated.
- Cockpit canopy weight is 50 kg and it has no lock in the open position, for this reason the canopy may to spontaneously close in a deep dive. Also, it is impossible to open or close canopy at high speed due to strong airflow. The canopy has no emergency release, so bail out requires the speed drop before it.
- Airplane is equipped with a joint salvo controller both for bombs and rockets, it has three release/fire modes: single launch, launch two in a salvo or launch four in a salvo.
- The gunsight is installed on a sliding bar which allows the pilot to extend the gunsight towards the pilot allowing fo an increase in the field of view through the gunsight.
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Re: IL-2 Sturmovik Flugzeuginformationen - VVS

Beitrag von I/JG27_Zimmi » Di 27 Dez 2016, 18:08

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Indicated stall speed in flight configuration: 175..200 km/h
Indicated stall speed in takeoff/landing configuration: 148..169 km/h

Dive speed limit: 790 km/h
Maximum load factor: 11 G
Stall angle of attack in flight configuration: 13.9 °
Stall angle of attack in landing configuration: 9.8 °

Maximum true air speed at sea level, engine mode - Nominal: 434 km/h
Maximum true air speed at 2000 m, engine mode - Nominal: 476 km/h
Maximum true air speed at 5000 m, engine mode - Nominal: 521 km/h

Service ceiling: 9100 m
Climb rate at sea level: 9.3 m/s
Climb rate at 3000 m: 8.4 m/s
Climb rate at 6000 m: 5.6 m/s

Maximum performance turn at sea level: 30.5 s, at 270 km/h IAS.
Maximum performance turn at 3000 m: 39.9 s, at 270 km/h IAS.

Flight endurance at 3000 m: 3.7 h, at 300 km/h IAS.

Takeoff speed: 160..200 km/h
Glideslope speed: 220..240 km/h
Landing speed: 155..165 km/h
Landing angle: 12.5 °

Note 1: the data provided is for international standard atmosphere (ISA).
Note 2: flight performance ranges are given for possible aircraft mass ranges.
Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass.
Note 4: climb rates and turn times are given for Nominal power.

Engine:
Model: M-105RA
Maximum power in Nominal mode at sea level: 1020 HP
Maximum power in Nominal mode at 2000 m: 1100 HP
Maximum power in Nominal mode at 4000 m: 1050 HP

Engine modes:
Nominal (unlimited time): 2700 RPM, 910 mm Hg

Water rated temperature in engine output: 70..85 °C
Water maximum temperature in engine output: 100 °C
Oil rated temperature in engine output: 90..100 °C
Oil maximum temperature in engine output: 110 °C

Supercharger gear shift altitude: 2700 m

Empty weight: 6078 kg
Minimum weight (no ammo, 10% fuel): 6640 kg
Standard weight: 7697 kg
Maximum takeoff weight: 8712 kg
Fuel load: 1129 kg / 1505 l
Useful load: 2634 kg

Forward-firing armament:
12.7mm machine gun "UB", 150 rounds, 1000 rounds per minute, nose-mounted
7.62mm machine gun "ShKAS", 450 rounds, 1800 rounds per minute, nose-mounted

Defensive armament:
Top: 7.62mm machine gun "ShKAS", 750 rounds, 1800 rounds per minute
Belly: 12.7mm machine gun "UB", 200 rounds, 1000 rounds per minute
Side: 7.62mm machine gun "ShKAS", 225 rounds, 1800 rounds per minute

Bombs:
Up to 10 x 104 kg general purpose bombs "FAB-100M"
Up to 4 x 254 kg general purpose bombs "FAB-250sv"
Up to 2 x 512 kg general purpose bombs "FAB-500M"

Rockets:
10 x 23 kg rockets "ROS-132", HE payload mass 9.1 kg

Length: 12.69 m
Wingspan: 17.12 m
Wing surface: 40.8 m^2

Combat debut: July 1941

Additional airplane configurations list:

10 x 104 kg General Purpose Bombs FAB-100M
Additional mass: 1040 kg
Ammunition mass: 1040 kg
Estimated speed loss before drop: 23 km/h
Estimated speed loss after drop: 0 km/h

4 x 254 kg General Purpose Bombs FAB-250sv
Additional mass: 1016 kg
Ammunition mass: 1016 kg
Estimated speed loss before drop: 33 km/h
Estimated speed loss after drop: 0 km/h

2 x 512 kg General Purpose Bombs FAB-500M
Additional mass: 1024 kg
Ammunition mass: 1024 kg
Estimated speed loss before drop: 48 km/h
Estimated speed loss after drop: 0 km/h

10 x 132mm High Explosive unguided rockets ROS-132
Additional mass: 280 kg
Ammunition mass: 230 kg
Racks mass: 50 kg
Estimated speed loss before launch: 31 km/h
Estimated speed loss after launch: 20 km/h

RPK-2 fixed loop radio compass for navigation with radio beacons
Additional mass: 20 kg
Estimated speed loss: 2 km/h

Operation features:
- Engine has a two-stage mechanical supercharger which must be manually switched at 2700m altitude.
- Engine mixture control is manual; it is necessary to lean the mixture if altitude is more than 3-4 km for optimal engine operation. Also, leaning the mixture allows a reduction in fuel consumption during flight.
- Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. The governor is electrically actuated and takes a long time to reach the required revolutions, up to 45 seconds when going from minimum to maximum.
- Water and oil radiator shutter control is manual.
- Airplane has trimmers for all flight-controls: pitch, roll, yaw.
- Airplane has fence-type airbrakes which are located under the wing and used to slow the descent during steep dive bombing.
- Landing flaps have electro-hydraulic actuator and they can be extended to any angle up to 50°. When landing and the flaps are fully extended the angle of attack for a stall is less than landing pitch angle. For this reason, it is prohibited to extend flaps to more than to 35° (70%) on landing.
- Airplane has automatically controlled horizontal stabilizer. The automatic control system adjusts the stabilizer angle depending on landing flaps extended angle.
- Airplane tail wheel rotates freely and does not have a lock. For this reason, it is necessary to confidently and accurately operate the rudder pedals during the takeoff and landing.
- Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other.
- Airplane has three fuel gauges which shows the level in the fuselage fuel tank, left wing tanks and right wing tanks.
- Cockpit canopy have an emergency release system for bailouts.
- Airplane is equipped with a bomb salvo controller, it has four release modes: drop single, drop two in a salvo, drop four in a salvo or drop all bombs in salvo. There is also a controller for a drop delay between each bomb in the salvo.
- When rockets are installed a salvo controller can be used, it has three launch modes: single fire, fire two in a salvo or fire four in a salvo. Aircraft has a fire control system that is designed for eight rockets. However, for added punch, ten rockets were typically loaded. In that case, the ninth rocket will fire with the seventh and the tenth will fire with the eighth.
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Re: IL-2 Sturmovik Flugzeuginformationen - VVS

Beitrag von I/JG27_Zimmi » Mi 28 Dez 2016, 05:17

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Indicated stall speed in flight configuration: 163..189 km/h
Indicated stall speed in takeoff/landing configuration: 138..168 km/h
Dive speed limit: 750 km/h
Maximum load factor: 11 G
Stall angle of attack in flight configuration: 18 °
Stall angle of attack in landing configuration: 15 °

Maximum true air speed at sea level, engine mode - Nominal: 505 km/h
Maximum true air speed at 2000 m, engine mode - Nominal: 548 km/h
Maximum true air speed at 4000 m, engine mode - Nominal: 573 km/h

Service ceiling: 10500 m
Climb rate at sea level: 14.9 m/s
Climb rate at 3000 m: 13.3 m/s
Climb rate at 6000 m: 8 m/s

Maximum performance turn at sea level: 22.2 s, at 280 km/h IAS.
Maximum performance turn at 3000 m: 28.9 s, at 270 km/h IAS.

Flight endurance at 3000 m: 2.2 h, at 350 km/h IAS.

Takeoff speed: 165..200 km/h
Glideslope speed: 200..210 km/h
Landing speed: 140..160 km/h
Landing angle: 12.8 °

Note 1: the data provided is for international standard atmosphere (ISA).
Note 2: flight performance ranges are given for possible aircraft mass ranges.
Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass.
Note 4: climb rates and turn times are given for Nominal power.

Engine:
Model: M-105PF
Maximum power in Nominal mode at sea level: 1200 HP
Maximum power in Nominal mode at 800 m: 1260 HP
Maximum power in Nominal mode at 2700 m: 1200 HP

Engine modes:
Nominal (unlimited time): 2700 RPM, 1050 mm Hg

Water rated temperature in engine output: 70..85 °C
Water maximum temperature in engine output: 100 °C
Oil rated temperature in engine output: 90..100 °C
Oil maximum temperature in engine output: 115 °C

Supercharger gear shift altitude: 2500 m

Empty weight: 2620 kg
Minimum weight (no ammo, 10% fuel): 2773 kg
Standard weight: 3157 kg
Maximum takeoff weight: 3701 kg
Fuel load: 348 kg / 467 l
Useful load: 1081 kg

Forward-firing armament:
20mm gun "SsVAK", 160 rounds, 800 rounds per minute, nose-mounted
12.7mm machine gun "UB", 200 rounds, 1000 rounds per minute, synchronized
23mm gun "VYa-23", 90 rounds, 600 rounds per minute, nose-mounted (modification)
37mm gun "Sh-37", 20 rounds, 185 rounds per minute, nose-mounted (modification)

Bombs:
2 x 50 kg general purpose bombs "FAB-50sv"
2 x 104 kg general purpose bombs "FAB-100M"

Rockets:
6 x 7 kg rockets "ROS-82", HE payload mass 2.52 kg

Length: 8.84 m
Wingspan: 9.8 m
Wing surface: 17.51 m^2

Combat debut: May 1942

Additional airplane configurations list:

VYa-23 23mm motor-gun with 90 rounds
Additional mass: 35 kg
Ammunition mass: 45 kg
Gun mass: 66 kg
Estimated speed loss: 0 km/h

Sh-37 37mm motor-gun with 20 rounds
Additional mass: 106 kg
Ammunition mass: 25 kg
Gun mass: 169 kg
Estimated speed loss: 2 km/h

2 x 50 kg General Purpose Bombs FAB-50sv
Additional mass: 120 kg
Ammunition mass: 100 kg
Racks mass: 20 kg
Estimated speed loss before drop: 20 km/h
Estimated speed loss after drop: 12 km/h

2 x 104 kg General Purpose Bombs FAB-100M
Additional mass: 228 kg
Ammunition mass: 208 kg
Racks mass: 20 kg
Estimated speed loss before drop: 27 km/h
Estimated speed loss after drop: 12 km/h

6 x 82mm High Explosive unguided rockets ROS-82
Additional mass: 60 kg
Ammunition mass: 42 kg
Racks mass: 18 kg
Estimated speed loss before launch: 23 km/h
Estimated speed loss after launch: 17 km/h

Operation features:
- Engine has a two-stage mechanical supercharger which must be manually switched at 2500m altitude.
- Engine mixture control is manual, it is necessary to lean the mixture if altitude is more than 3-4 km for optimal engine operation. Also, leaning the mixture allows a reduction in fuel consumption during flight.
- Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM.
- Water and oil radiator shutters is manually controlled.
- Airplane has trimmers for all flight-controls: pitch, roll, yaw.
- Landing flaps have a hydraulic actuator and they can be extended to any angle up to 60°.
- Airplane tail wheel rotates freely and does not have a lock. For this reason, it is necessary to confidently and accurately operate the rudder pedals during the takeoff and landing.
- Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other.
- Airplane has a fuel gauge which shows total remaining fuel.
- Cockpit canopy has a weak lock when in the opened position, for this reason the canopy may spontaneously close in a deep dive. Also, it is impossible to open or close canopy at high speed due to strong airflow. The canopy has no emergency release, so bail out requires the speed drop before it.
- The control system of wing-mounted bomb racks only allows the dropping of bombs one by one.
- When rockets are installed a salvo controller is used, it has three launch modes: single fire, fire two in a salvo or fire four in a salvo.
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Re: IL-2 Sturmovik Flugzeuginformationen - VVS

Beitrag von I/JG27_Zimmi » Mi 28 Dez 2016, 05:20

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Indicated stall speed in flight configuration: 155..171 km/h
Indicated stall speed in takeoff/landing configuration: 133..146 km/h
Dive speed limit: 720 km/h
Maximum load factor: 10.3 G
Stall angle of attack in flight configuration: 18 °
Stall angle of attack in landing configuration: 15.6 °

Maximum true air speed at sea level, engine mode - Nominal, 2550 RPM: 514 km/h
Maximum true air speed at 2000 m, engine mode - Nominal, 2700 RPM: 549 km/h
Maximum true air speed at 4000 m, engine mode - Nominal, 2700 RPM: 582 km/h

Service ceiling: 10200 m
Climb rate at sea level: 16.9 m/s
Climb rate at 3000 m: 15.0 m/s
Climb rate at 6000 m: 9.4 m/s

Maximum performance turn at sea level: 19.2 s, at 270 km/h IAS.
Maximum performance turn at 3000 m: 24.6 s, at 270 km/h IAS.

Flight endurance at 3000 m: 1.9 h, at 350 km/h IAS.

Takeoff speed: 160..190 km/h
Glideslope speed: 195..205 km/h
Landing speed: 135..145 km/h
Landing angle: 12 °

Note 1: the data provided is for international standard atmosphere (ISA).
Note 2: flight performance ranges are given for possible aircraft mass ranges.
Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass.
Note 4: climb rates and turn times are given for Nominal (2700 RPM) power.

Engine:
Model: M-105PF
Maximum power in Nominal mode (2550 RPM) at sea level: 1240 HP
Maximum power in Nominal mode (2700 RPM) at sea level: 1210 HP
Maximum power in Nominal mode (2700 RPM) at 800 m: 1260 HP
Maximum power in Nominal mode (2700 RPM) at 2700 m: 1200 HP

Engine modes:
Nominal (unlimited time): 2550/2700 RPM, 1050 mm Hg

Water rated temperature in engine output: 70..85 °C
Water maximum temperature in engine output: 100 °C
Oil rated temperature in engine output: 90..100 °C
Oil maximum temperature in engine output: 115 °C

Supercharger gear shift altitude: 2300 m

Empty weight: 2365 kg
Minimum weight (no ammo, 10% fuel): 2583 kg
Standard weight: 2932 kg
Maximum takeoff weight: 3170 kg
Fuel load: 304 kg / 408 l
Useful load: 805 kg

Forward-firing armament:
20mm gun "SsVAK", 120 rounds, 800 rounds per minute, nose-mounted
2 x 7.62mm machine gun "ShKAS", 750 rounds, 1800 rounds per minute, synchronized

Bombs:
2 x 50 kg general purpose bombs "FAB-50sv"
2 x 104 kg general purpose bombs "FAB-100M"

Rockets:
Up to 6 x 7 kg rockets "ROS-82", HE payload mass 2.52 kg

Length: 8.5 m
Wingspan: 10 m
Wing surface: 17.15 m^2

Combat debut: May 1942

Additional airplane configurations list:

2 x 50 kg General Purpose Bombs FAB-50sv
Additional mass: 120 kg
Ammunition mass: 100 kg
Racks mass: 20 kg
Estimated speed loss before drop: 20 km/h
Estimated speed loss after drop: 12 km/h

2 x 104 kg General Purpose Bombs FAB-100M
Additional mass: 228 kg
Ammunition mass: 208 kg
Racks mass: 20 kg
Estimated speed loss before drop: 27 km/h
Estimated speed loss after drop: 12 km/h

2 x 82mm High Explosive unguided rockets ROS-82
Additional mass: 60 kg
Ammunition mass: 42 kg
Racks mass: 18 kg
Estimated speed loss before launch: 8 km/h
Estimated speed loss after launch: 6 km/h

6 x 82mm High Explosive unguided rockets ROS-82
Additional mass: 60 kg
Ammunition mass: 42 kg
Racks mass: 18 kg
Estimated speed loss before launch: 23 km/h
Estimated speed loss after launch: 17 km/h

RPK-10 fixed loop radio compass for navigation with radio beacons
Additional mass: 10 kg
Estimated speed loss: 0 km/h

Operation features:
- Engine has a two-stage mechanical supercharger which must be manually switched at 2300m altitude.
- Engine mixture control is manual; it is necessary to lean the mixture if altitude is more than 3-4 km for optimal engine operation. Also, leaning the mixture allows a reduction in fuel consumption during flight.
- Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM.
- Water and oil radiator shutter control is manual.
- Airplane has only a flight-control trimmer on the pitch.
- Landing flaps have a pneumatic actuator. Flaps can only be fully extended; gradual extending is impossible. Due to the weak force of the actuator the extended landing flaps may be pressed upwards by the airflow if the airspeed is more than 220 km/h. Remember that the flaps will not extend fully in case of high speed. In case of a high-speed landing approach the flaps may extend a few steps further right before landing.
- Airplane has a manual control for the tailwheel lock. The unlocked tailwheel has a 90° turn limit. The tailwheel should be locked when taxiing straight for a long distance and before takeoff and landing.
- Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other.
- Fuel gauges are installed on left and right wing fuel tanks, outside of the cockpit. They show remaining fuel level only when there is less than 80 liters of fuel left in the tank.
- It is impossible to open or close the canopy at high speed due to strong airflow. The canopy has no emergency release, so bail out requires the speed drop before it.
- The control system for the wing-mounted bomb racks only allows releasing of both bombs together.
- When rockets are installed a salvo controller can be used, it has three launch modes: single fire, fire two in a salvo or fire four in a salvo.
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Re: IL-2 Sturmovik Flugzeuginformationen - VVS

Beitrag von I/JG27_Zimmi » Mi 28 Dez 2016, 05:21

Bild

Indicated stall speed in flight configuration: 138..158 km/h
Indicated stall speed in takeoff/landing configuration: 130..148 km/h
Dive speed limit: 570 km/h
Maximum load factor: 10.5 G
Stall angle of attack in flight configuration: 19.4 °
Stall angle of attack in landing configuration: 17.5 °

Maximum true air speed at sea level, engine mode - Boosted: 400 km/h
Maximum true air speed at sea level, engine mode - Nominal: 380 km/h
Maximum true air speed at 2500 m, engine mode - Nominal: 414 km/h

Service ceiling: 6000 m
Climb rate at sea level: 7.1 m/s
Climb rate at 3000 m: 5.6 m/s
Climb rate at 6000 m:m/s

Maximum performance turn at sea level: 25.7 s, at 250 km/h IAS.
Maximum performance turn at 3000 m: 37.3 s, at 250 km/h IAS.

Flight endurance at 3000 m: 1.7 h, at 300 km/h IAS.

Takeoff speed: 150..190 km/h
Glideslope speed: 185..195 km/h
Landing speed: 135..145 km/h
Landing angle: 11.7 °

Note 1: the data provided is for international standard atmosphere (ISA).
Note 2: flight performance ranges are given for possible aircraft mass ranges.
Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass.
Note 4: climb rates are given for Nominal power, turn times are given for Boosted power.

Engine:
Model: AM-38
Maximum power in Boosted mode at sea level: 1600 HP
Maximum power in Nominal mode at sea level: 1500 HP
Maximum power in Nominal mode at 1650 m: 1500 HP

Engine modes:
Nominal (unlimited time): 2050 RPM, 1180 mm Hg
Boosted power (up to 10 minutes): 2150 RPM, 1280 mm Hg

Water rated temperature in engine output: 80..110 °C
Water maximum temperature in engine output: 120 °C
Oil rated temperature in engine intake: 40..80 °C
Oil maximum temperature in engine intake: 85 °C
Oil rated temperature in engine output: 115 °C
Oil maximum temperature in engine output: 120 °C

Supercharger gear shift altitude: single gear

Empty weight: 4462 kg
Minimum weight (no ammo, 10% fuel): 4651 kg
Standard weight: 5294 kg
Maximum takeoff weight: 6127 kg
Fuel load: 535 kg / 730 l
Useful load: 1665 kg

Forward-firing armament:
2 x 20mm gun "SsVAK", 250 rounds, 800 rounds per minute, wing-mounted
2 x 7.62mm machine gun "ShKAS", 750 rounds, 1800 rounds per minute, wing-mounted
2 x 23mm gun "VYa-23", 150 rounds, 600 rounds per minute, wing-mounted (modification)
2 x 37mm gun "Sh-37", 40 rounds, 185 rounds per minute, wing-mounted (modification)

Defensive armament:
Backward: 7.62mm machine gun "ShKAS", 500 rounds, 1800 rounds per minute (modification)

Bombs:
Up to 6 x 50 kg general purpose bombs "FAB-50sv"
Up to 6 x 104 kg general purpose bombs "FAB-100M"
2 x 254 kg general purpose bombs "FAB-250sv"

Rockets:
8 x 7 kg rockets "ROS-82", HE payload mass 2.5 kg
8 x 15 kg rockets "RBS-82", HEAT payload mass 7.2 kg
8 x 42 kg rockets "ROFS-132", HE payload mass 21.3 kg

Length: 11.5 m
Wingspan: 14.6 m
Wing surface: 38.5 m^2

Combat debut: June 1942

Additional airplane configurations list:

2 VYa-23 23mm wing-mounted guns with 150 rounds per each
Additional mass: 91 kg
Ammunition mass: 170 kg
Guns mass: 132 kg
Estimated speed loss: 1 km/h

2 gun pods with Sh-37 37mm guns with 40 rounds per each
Additional mass: 495 kg
Ammunition mass: 101 kg
Guns mass: 605 kg
Estimated speed loss: 19 km/h

2 x 254 kg General Purpose Bombs FAB-250sv
Additional mass: 538 kg
Ammunition mass: 508 kg
Racks mass: 30 kg
Estimated speed loss before drop: 18 km/h
Estimated speed loss after drop: 7 km/h

8 x 82mm Armour Piercing unguided rockets RBS-82 or 8 x 132mm High Explosive unguided rockets ROFS-132
RBS-82:
Additional mass: 144 kg
Ammunition mass: 120 kg
Racks mass: 24 kg
Estimated speed loss before launch: 10 km/h
Estimated speed loss after launch: 7 km/h
ROFS-132:
Additional mass: 376 kg
Ammunition mass: 336 kg
Racks mass: 40 kg
Estimated speed loss before launch: 18 km/h
Estimated speed loss after launch: 9 km/h

Rear turret with ShKAS 7.62mm machinegun with 500 rounds
Additional mass: 130 kg
Estimated speed loss: 40 km/h

Operation features:
- Engine has a boost mode which is engaging by setting mixture control lever to maximum position.
- Engine has a single stage mechanical supercharger which does not require manual control.
- Engine mixture control is automatic when the mixture lever is set to the intermediate (50%) position. It is possible to manually lean the mixture by moving the control lever to less than 50%. This will lower fuel consumption during flight.
- Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM.
- Water and oil radiator shutter control is manual. Airplane has armored oil radiator shutters which should to be closed on start of ground attack to reduce possibility of combat damage. After finishing the attack, it is necessary to re-open the shutters to the required position.
- Airplane has only the pitch flight-control trimmer.
- Landing flaps have a pneumatic actuator. Flaps can only be fully extended; gradual extending is impossible. Due to the weak force of the actuator the extended landing flaps may be pressed upwards by the airflow if the airspeed is more than 220 km/h. Remember that the flaps will not extend fully in case of high speed. In case of a high-speed landing approach the flaps may extend a few steps further right before landing.
- Airplane has a manual tail wheel lock. Wheel should be locked when taxiing straight for a long distance and before takeoff and landing.
- Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other.
- Airplane has a fuel gauge which shows the amount of remaining fuel in the front or bottom fuel tank depending on the switch position. In game the fuel indication switch changes by itself during horizontal flight by every 10 seconds. Rear fuel tank level is not indicated.
- Cockpit canopy weight is 50 kg and it has no lock in the open position, for this reason the canopy may to spontaneously close in a deep dive. Also, it is impossible to open or close canopy at high speed due to strong airflow. The canopy has no emergency release, so bail out requires the speed drop before it.
- Airplane is equipped with a bomb salvo controller, it has three release modes: single drop, drop two in a salvo or drop four in a salvo.
- Airplane is equipped with a rockets salvo controller, it has three launch modes: single fire, fire two in a salvo or fire four in a salvo.
- The gunsight is installed on a sliding bar which allows the pilot to extend the gunsight towards the pilot allowing fo an increase in the field of view through the gunsight.
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Re: IL-2 Sturmovik Flugzeuginformationen - VVS

Beitrag von I/JG27_Zimmi » Mi 28 Dez 2016, 05:22

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Indicated stall speed in flight configuration: 175..200 km/h
Indicated stall speed in takeoff/landing configuration: 148..169 km/h
Dive speed limit: 790 km/h
Maximum load factor: 11 G
Stall angle of attack in flight configuration: 13.9 °
Stall angle of attack in landing configuration: 9.8 °

Maximum true air speed at sea level, engine mode - Nominal: 446 km/h
Maximum true air speed at 2000 m, engine mode - Nominal: 476 km/h
Maximum true air speed at 5000 m, engine mode - Nominal: 498 km/h

Service ceiling: 8000 m
Climb rate at sea level: 10.4 m/s
Climb rate at 3000 m: 7.8 m/s
Climb rate at 6000 m: 3.0 m/s

Maximum performance turn at sea level: 29.9 s, at 270 km/h IAS.
Maximum performance turn at 3000 m: 40.3 s, at 270 km/h IAS.

Flight endurance at 3000 m: 2.8 h, at 300 km/h IAS.

Takeoff speed: 160..200 km/h
Glideslope speed: 220..240 km/h
Landing speed: 155..165 km/h
Landing angle: 12.5 °

Note 1: the data provided is for international standard atmosphere (ISA).
Note 2: flight performance ranges are given for possible aircraft mass ranges.
Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass.
Note 4: climb rates and turn times are given for Nominal power.

Engine:
Model: M-105RF
Maximum power in Nominal mode at sea level: 1200 HP
Maximum power in Nominal mode at 800 m: 1260 HP
Maximum power in Nominal mode at 2700 m: 1200 HP

Engine modes:
Nominal (unlimited time): 2700 RPM, 1050 mm Hg

Water rated temperature in engine output: 70..85 °C
Water maximum temperature in engine output: 100 °C
Oil rated temperature in engine output: 90..100 °C
Oil maximum temperature in engine output: 115 °C

Supercharger gear shift altitude: 2300 m

Empty weight: 6089 kg
Minimum weight (no ammo, 10% fuel): 6643 kg
Standard weight: 7685 kg
Maximum takeoff weight: 8701 kg
Fuel load: 1113 kg / 1484 l
Useful load: 2612 kg

Forward-firing armament:
12.7mm machine gun "UB", 150 rounds, 1000 rounds per minute, nose-mounted
7.62mm machine gun "ShKAS", 450 rounds, 1800 rounds per minute, nose-mounted

Defensive armament:
Top: 12.7mm machine gun "UB", 200 rounds, 1000 rounds per minute
Belly: 12.7mm machine gun "UB", 200 rounds, 1000 rounds per minute
Side: 7.62mm machine gun "ShKAS", 225 rounds, 1800 rounds per minute
Top turret: 12.7mm machine gun "UB", 200 rounds, 1000 rounds per minute (modification "series 110")

Bombs:
Up to 10 x 104 kg general purpose bombs "FAB-100M"
Up to 4 x 254 kg general purpose bombs "FAB-250sv"
Up to 2 x 512 kg general purpose bombs "FAB-500M"

Rockets:
10 x 23 kg rockets "ROS-132", HE payload mass 9.1 kg

Length: 12.69 m
Wingspan: 17.12 m
Wing surface: 40.8 m^2

Combat debut: May 1942

Additional airplane configurations list:

10 x 104 kg General Purpose Bombs FAB-100M
Additional mass: 1040 kg
Ammunition mass: 1040 kg
Estimated speed loss before drop: 23 km/h
Estimated speed loss after drop: 0 km/h

4 x 254 kg General Purpose Bombs FAB-250sv
Additional mass: 1016 kg
Ammunition mass: 1016 kg
Estimated speed loss before drop: 33 km/h
Estimated speed loss after drop: 0 km/h

2 x 512 kg General Purpose Bombs FAB-500M
Additional mass: 1024 kg
Ammunition mass: 1024 kg
Estimated speed loss before drop: 48 km/h
Estimated speed loss after drop: 0 km/h

10 x 132mm High Explosive unguided rockets ROS-132
Additional mass: 280 kg
Ammunition mass: 230 kg
Racks mass: 50 kg
Estimated speed loss before launch: 31 km/h
Estimated speed loss after launch: 20 km/h

VUB-1 rear wide-angle turret with UBT 12.7mm machinegun with 200 rounds
Additional mass: 0 kg
Estimated speed loss: 5 km/h

Operation features:
- Engine has a two-stage mechanical supercharger which must be manually switched at 2300m altitude.
- Engine mixture control is manual; it is necessary to lean the mixture if altitude is more than 3-4 km for optimal engine operation. Also, leaning the mixture allows a reduction in fuel consumption during flight.
- Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM.
- Water radiator shutter control is manual. Oil radiator shutters are fixed.
- Airplane has trimmers for all flight-controls: pitch, roll, yaw.
- Airplane has fence-type airbrakes which are located under the wing and used to slow the descent during steep dive bombing.
- Landing flaps have electro-hydraulic actuator and they can be extended to any angle up to 50°. When landing and the flaps are fully extended the angle of attack for a stall is less than landing pitch angle. For this reason, it is prohibited to extend flaps to more than to 35° (70%) on landing.
- Airplane has automatically controlled horizontal stabilizer. The automatic control system adjusts the stabilizer angle depending on landing flaps extended angle.
- Airplane tail wheel rotates freely and does not have a lock. For this reason, it is necessary to confidently and accurately operate the rudder pedals during the takeoff and landing.
- Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other.
- Airplane has a fuel gauge which shows total fuel remaining.
- Cockpit canopy have an emergency release system for bailouts.
- Airplane is equipped with a bomb salvo controller, it has four release modes: drop single, drop two in a salvo, drop four in a salvo or drop all bombs in salvo. There is also a controller for a drop delay between each bomb in the salvo.
- When rockets are installed a salvo controller can be used, it has three launch modes: single fire, fire two in a salvo or fire four in a salvo. Aircraft has a fire control system that is designed for eight rockets. However, for added punch, ten rockets were typically loaded. In that case, the ninth rocket will fire with the seventh and the tenth will fire with the eighth.
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Re: IL-2 Sturmovik Flugzeuginformationen - VVS

Beitrag von I/JG27_Zimmi » Mi 28 Dez 2016, 05:23

Bild

Indicated stall speed in flight configuration: 153..176 km/h
Indicated stall speed in takeoff/landing configuration: 141..164 km/h

Dive speed limit: 860 km/h
Maximum load factor: 12.2 G
Stall angle of attack in flight configuration: 14 °
Stall angle of attack in landing configuration: 12.6 °

Maximum true air speed at sea level, engine mode - Take-off: 494 km/h
Maximum true air speed at 5000 m, engine mode - Take-off: 601 km/h

Service ceiling: 9200 m
Climb rate at sea level: 12.5 m/s
Climb rate at 3000 m: 10 m/s
Climb rate at 6000 m: 3.7 m/s

Maximum performance turn at sea level: 24.3 s, at 270 km/h IAS.
Maximum performance turn at 3000 m: 36.1 s, at 270 km/h IAS.

Flight endurance at 3000 m: 2.8 h, at 350 km/h IAS.

Takeoff speed: 160..190 km/h
Glideslope speed: 210..220 km/h
Landing speed: 140..145 km/h
Landing angle: 13.9 °

Note 1: the data provided is for international standard atmosphere (ISA).
Note 2: flight performance ranges are given for possible aircraft mass ranges.
Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass.
Note 4: climb rates are given for Take-off power, turn times are given for Maximum possible power.

Engine:
Model: V-1710-39
Maximum power in Maximum Possible power mode at sea level: 1470 HP
Maximum power in Take-off mode at sea level: 1150 HP
Maximum power in Nominal mode at sea level: 900 HP
Maximum power in Combat mode at 12000 feet: 1150 HP
Maximum power in Nominal mode at 10800 feet: 1000 HP

Engine modes:
Nominal (unlimited time): 2600 RPM, 37.2 inch Hg
Combat power (up to 5 minutes): 3000 RPM, 42 inch Hg
Take-off power (up to 2 minutes): 3000 RPM, 45.5 inch Hg
Maximum Possible power (prohibited by flight manual): 3000 RPM, 56.0 inch Hg

Water rated temperature in engine output: 105..115 °C
Water maximum temperature in engine output: 125 °C
Oil rated temperature in engine intake: 70..85 °C
Oil maximum temperature in engine intake: 90 °C

Supercharger gear shift altitude: single gear

Empty weight: 3073 kg
Minimum weight (no ammo, 10% fuel): 3264.2 kg
Standart weight: 3819.1 kg
Maximum takeoff weight: 4414 kg
Fuel load: 404 kg / 561 l
Useful load: 1341 kg

Forward-firing armament:
6 x 12.7mm machine gun "M2.50", 235 rounds, 850 rounds per minute, wing-mounted

Bombs:
254 kg general purpose bomb "FAB-250sv"
512 kg general purpose bomb "FAB-500M"

Rockets:
4 x 7 kg rockets "ROS-82", HE payload mass 2.52 kg

Length: 9.05 m
Wingspan: 11.4 m
Wing surface: 21.92 m^2

Combat debut: December 1941

Additional airplane configurations list:

Removal of 2 external wing-mounted machine guns to reduce total weight
Weight savings: 156 kg
Removed ammunition mass: 64 kg
Removed guns mass: 92 kg
Estimated additional speed: 3 km/h

Additional ammo for machine guns: 312 for internal ones, 291 for middle ones, 240 for external ones (instead of 235 per each) or 615 per each for 4x MG.
6 machineguns:
Additional mass: 38 kg
Estimated speed loss: 0 km/h
4 machineguns:
Additional mass: 207 kg
Estimated speed loss: 2 km/h

254 kg General Purpose Bomb FAB-250sv
Additional mass: 264 kg
Ammunition mass: 254 kg
Rack mass: 10 kg
Estimated speed loss before drop: 19 km/h
Estimated speed loss after drop: 7 km/h

254 kg General Purpose Bomb FAB-500M
Additional mass: 522 kg
Ammunition mass: 512 kg
Rack mass: 10 kg
Estimated speed loss before drop: 36 km/h
Estimated speed loss after drop: 7 km/h

4 x 82mm High Explosive unguided rockets ROS-82
Additional mass: 40 kg
Ammunition mass: 28 kg
Racks mass: 12 kg
Estimated speed loss before launch: 13 km/h
Estimated speed loss after launch: 10 km/h

Operation features:
- Engine has no manifold pressure automatic governor. For this reason, manifold pressure not only depends on throttle position, but also from RPM and altitude. This requires additional checking of manifold pressure to not cause engine damage.
- Engine has a single-stage mechanical supercharger which does not require manual control.
- Engine is equipped with an automatic fuel mixture control which maintains optimal mixture if mixture lever is set to Auto Rich (66%) position. To use automatic mixture leaning to reduce fuel consumption during flight it is necessary to set mixture lever to Auto Lean (33%) position. In the case of mulfunction of the automatic mixture control the mixture lever should be set to Full Rich (100%) position. To stop the engine mixture lever should be set to the Cut Off (0%) position.
- Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. Also it is possible to turn off the governor and control propeller pitch manually.
- Water and oil radiators shutters are joint with engine cowl outlet shutters and manually operated.
- Airplane has a very small stability margin in yaw. When angle of side slip is more than 12° plane becomes unstable in yaw and starts to increase the side slip angle by itself. Because of this, it is necessary to accurately operate the rudder pedals and pay attention to the side slip indicator.
- Airplane has trimmers for all flight-controls: pitch, roll, yaw.
- Landing flaps have a hydraulic actuator and they can be extended to any angle up to 45°.
- Airplane has a tailwheel control system which is unlocked by the rudder if the rudder pedal is pressed more than half of its range. The tailwheel remains locked if pedals are deflected less than half way. Because of this, it is necessary to avoid large rudder pedal inputs when moving at high speed.
- Airplane has independent left and right hydraulic wheel brakes. To brake it is necessary to push upper part of the rudder pedal.
- Airplane is equipped with a parking brake system.
- Airplane has three fuel gauges which shows the level in each fuel tank.
- It is impossible to open or close canopy at high speed due to strong airflow. The canopy has an emergency release system for bail out.
- Airplane is equipped with mechanical releasing system for a single bomb.
- When rockets are installed a salvo controller can be used, it has three launch modes: single fire, fire two in a salvo or fire four in a salvo.
- The gunsight has a sliding sun-filter. There is also a back-up mechanical sight which can be used if main sight is damaged.
OLt. Zimmermann
Gruppenkommandeur

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Re: IL-2 Sturmovik Flugzeuginformationen - VVS

Beitrag von I/JG27_Zimmi » Mi 28 Dez 2016, 05:23

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Indicated stall speed in flight configuration: 165..183 km/h
Indicated stall speed in takeoff/landing configuration: 147..162 km/h
Dive speed limit: 720 km/h
Maximum load factor: 10 G
Stall angle of attack in flight configuration: 22.7 °
Stall angle of attack in landing configuration: 15.1 °

Maximum true air speed at sea level, engine mode - Boosted: 544 km/h
Maximum true air speed at 3000 m, engine mode - Nominal: 571 km/h
Maximum true air speed at 6500 m, engine mode - Nominal: 603 km/h

Service ceiling: 9500 m
Climb rate at sea level: 18 m/s
Climb rate at 3000 m: 13.3 m/s
Climb rate at 6000 m: 8.2 m/s

Maximum performance turn at sea level: 23.4 s, at 270 km/h IAS.
Maximum performance turn at 3000 m: 35.3 s, at 270 km/h IAS.

Flight endurance at 3000 m: 1.9 h, at 350 km/h IAS.

Takeoff speed: 170..200 km/h
Glideslope speed: 200..210 km/h
Landing speed: 150..160 km/h
Landing angle: 13 °

Note 1: the data provided is for international standard atmosphere (ISA).
Note 2: flight performance ranges are given for possible aircraft mass ranges.
Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass.
Note 4: climb rates and turn times are given for Boosted power.

Engine:
Model: M-82
Maximum power in Boosted mode at sea level: 1700 HP
Maximum power in Nominal mode at sea level: 1400 HP
Maximum power in Nominal mode at 2100 m: 1550 HP
Maximum power in Nominal mode at 5300 m: 1335 HP

Engine modes:
Nominal (unlimited time): 2400 RPM, 950 mm Hg
Boosted power (up to 5 minutes): 2400 RPM, 1140 mm Hg

Oil rated temperature in engine output: 55..90 °C
Oil maximum temperature in engine output: 125 °C
Cylinder head rated temperature: 140..210 °C
Cylinder head maximum temperature: 215 °C

Supercharger gear shift altitude: 3500 m

Empty weight: 2648 kg
Minimum weight (no ammo, 10% fuel): 2928 kg
Standard weight: 3353 kg
Maximum takeoff weight: 3593 kg
Fuel load: 370 kg / 521 l
Useful load: 945 kg

Forward-firing armament:
2 x 20mm gun "SsVAK", 170 rounds, 800 rounds per minute, synchronized

Bombs:
2 x 50 kg general purpose bombs "FAB-50sv"
2 x 104 kg general purpose bombs "FAB-100M"

Length: 8.672 m
Wingspan: 9.8 m
Wing surface: 17.51 m^2

Combat debut: September 1942

Additional airplane configurations list:

Loadout variants: armour piercing (AP) or high-explosive (HE) rounds only

2 x 50 kg General Purpose Bombs FAB-50sv
Additional mass: 120 kg
Ammunition mass: 100 kg
Racks mass: 20 kg
Estimated speed loss before drop: 20 km/h
Estimated speed loss after drop: 12 km/h

2 x 104 kg General Purpose Bombs FAB-100M
Additional mass: 228 kg
Ammunition mass: 208 kg
Racks mass: 20 kg
Estimated speed loss before drop: 27 km/h
Estimated speed loss after drop: 12 km/h

Flat frontal section for better visibility
Additional mass: 2 kg
Estimated speed loss: 2 km/h

RPK-10 fixed loop radio compass for navigation with radio beacons
Additional mass: 10 kg
Estimated speed loss: 0 km/h

Operation features:
- Engine has a boost mode. To set boost mode it is necessary to push the boost knob and increase manifold pressure to 1140 mm Hg.
- Engine has a two-stage mechanical supercharger which must be manually switched at 3500m altitude.
- Engine mixture control is automatic when the mixture lever is set to maximum. It is possible to manually lean the mixture by moving the mixture control to less than maximum. This also reduces fuel consumption during flight.
- Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM.
- Oil radiator, air cooling intake and outlet shutters is manually controlled.
- Air cooling intake shutters should always be open. They should only be closed when there is a possibility of engine overcooling, for example in a dive with idle throttle.
- Airplane has trimmers for all flight-controls: pitch, roll, yaw.
- Airplane has automatic wing slats. They deploy when the high angle of attack increases which makes pre-stall softer.
- Landing flaps have a hydraulic actuator and they can be extended to any angle up to 60°.
- Airplane tail wheel rotates freely and does not have a lock. For this reason, it is necessary to confidently and accurately operate the rudder pedals during the takeoff and landing.
- Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other.
- Airplane has a fuel gauge which shows total remaining fuel.
- Cockpit canopy has a weak lock when in the opened position, for this reason the canopy may spontaneously close in a deep dive. Also, it is impossible to open or close canopy at high speed due to strong airflow. The canopy has no emergency release, so bail out requires the speed drop before it.
- The control system of wing-mounted bomb racks only allows the dropping of bombs one by one
OLt. Zimmermann
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Re: IL-2 Sturmovik Flugzeuginformationen - VVS

Beitrag von I/JG27_Zimmi » Mi 28 Dez 2016, 05:24

Bild

Indicated stall speed in flight configuration: 153..169 km/h
Indicated stall speed in takeoff/landing configuration: 132..145 km/h
Dive speed limit: 720 km/h
Maximum load factor: 10.3 G
Stall angle of attack in flight configuration: 18 °
Stall angle of attack in landing configuration: 15.6 °

Maximum true air speed at sea level, engine mode - Nominal, 2550 RPM: 530 km/h
Maximum true air speed at 2000 m, engine mode - Nominal, 2700 RPM: 567 km/h
Maximum true air speed at 4500 m, engine mode - Nominal, 2700 RPM: 600 km/h

Service ceiling: 10600 m
Climb rate at sea level: 17.0 m/s
Climb rate at 3000 m: 15.0 m/s
Climb rate at 6000 m: 9.5 m/s

Maximum performance turn at sea level: 19.0 s, at 270 km/h IAS.
Maximum performance turn at 3000 m: 24.1 s, at 270 km/h IAS.

Flight endurance at 3000 m: 2.0 h, at 350 km/h IAS.

Takeoff speed: 160..190 km/h
Glideslope speed: 195..205 km/h
Landing speed: 135..145 km/h
Landing angle: 12 °

Note 1: the data provided is for international standard atmosphere (ISA).
Note 2: flight performance ranges are given for possible aircraft mass ranges.
Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass.
Note 4: climb rates and turn times are given for Nominal (2700 RPM) power.

Engine:
Model: M-105PF
Maximum power in Nominal mode (2550 RPM) at sea level: 1240 HP
Maximum power in Nominal mode (2700 RPM) at sea level: 1210 HP
Maximum power in Nominal mode (2700 RPM) at 800 m: 1260 HP
Maximum power in Nominal mode (2700 RPM) at 2700 m: 1200 HP

Engine modes:
Nominal (unlimited time): 2550/2700 RPM, 1050 mm Hg

Water rated temperature in engine output: 70..85 °C
Water maximum temperature in engine output: 100 °C
Oil rated temperature in engine output: 90..100 °C
Oil maximum temperature in engine output: 115 °C

Supercharger gear shift altitude: 2300 m

Empty weight: 2322 kg
Minimum weight (no ammo, 10% fuel): 2543 kg
Standard weight: 2887 kg
Maximum takeoff weight: 3117 kg
Fuel load: 304 kg / 408 l
Useful load: 795 kg

Forward-firing armament:
20mm gun "SsVAK", 140 rounds, 800 rounds per minute, nose-mounted
12.7mm machine gun "UB", 220 rounds, 1000 rounds per minute, synchronized

Bombs:
2 x 50 kg general purpose bombs "FAB-50sv"
2 x 104 kg general purpose bombs "FAB-100M"

Length: 8.5 m
Wingspan: 10 m
Wing surface: 17.15 m^2

Combat debut: April 1943

Additional airplane configurations list:

2 x 50 kg General Purpose Bombs FAB-50sv
Additional mass: 120 kg
Ammunition mass: 100 kg
Racks mass: 20 kg
Estimated speed loss before drop: 23 km/h
Estimated speed loss after drop: 13 km/h

2 x 104 kg General Purpose Bombs FAB-100M
Additional mass: 228 kg
Ammunition mass: 208 kg
Racks mass: 20 kg
Estimated speed loss before drop: 31 km/h
Estimated speed loss after drop: 13 km/h

Landing light for night flights
Additional mass: 2 kg
Estimated speed loss: 0 km/h

RPK-10 fixed loop radio compass for navigation with radio beacons
Additional mass: 10 kg
Estimated speed loss: 0 km/h

Operation features:
- Engine has a two-stage mechanical supercharger which must be manually switched at 2300m altitude.
- Engine mixture control is manual; it is necessary to lean the mixture if altitude is more than 3-4 km for optimal engine operation. Also, leaning the mixture allows a reduction in fuel consumption during flight.
- Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM.
- Water and oil radiator shutter control is manual.
- Airplane has only a flight-control trimmer on the pitch.
- Landing flaps have a pneumatic actuator. Flaps can only be fully extended; gradual extending is impossible. Due to the weak force of the actuator the extended landing flaps may be pressed upwards by the airflow if the airspeed is more than 220 km/h. Remember that the flaps will not extend fully in case of high speed. In case of a high-speed landing approach the flaps may extend a few steps further right before landing.
- Airplane has a tailwheel control system which is unlocked by the rudder if the rudder pedal is pressed more than 75% of its range. The tailwheel remains locked if pedals are deflected less than 75%. Because of this, it is necessary to avoid large rudder pedal inputs when moving at high speed.
- Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other.
- Fuel gauges are installed on left and right wing fuel tanks, outside of the cockpit. They show remaining fuel level only when there is less than 80 liters of fuel left in the tank.
- It is impossible to open or close the canopy at high speed due to strong airflow. The canopy has no emergency release, so bail out requires the speed drop before it.
- The control system for the wing-mounted bomb racks only allows releasing of both bombs together
OLt. Zimmermann
Gruppenkommandeur

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