Mig-21-Flight Model - Check six

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Mig-21-FM-Identification-Rev. 14 Figure 11 Vcas (Km/h) Vcas (Kts) Mach Sustained Ng Sustained Ng (computed) Error 500 270 0.489 2.46 2.58 5% 550 297 0.538 2.74 2.86 4% 600 324 0.587 3.02 3.12 3% 650 351 0.634 3.29 3.35 2% 700 378 0.682 3.53 3.58 2% 750 405 0.730 3.76 3.78 1% 800 432 0.778 3.90 3.95 1% 850 459 0.826 4.06 4.05 0% 900 486 0.874 4.15 4.02 -3% 950 513 0.922 4.23 3.74 -11% Figure 12 Vcas (Km/h) Vcas (Kts) Mach Sustained Ng Sustained Ng (computed) Error 500 270 0.548 2.41 2.44 1% 550 297 0.600 2.65 2.69 1% 600 324 0.651 2.91 2.91 0% 650 351 0.702 3.14 3.13 0% 700 378 0.754 3.36 3.35 0% 750 405 0.805 3.56 3.56 0% 800 432 0.856 3.73 3.67 -2% Page - 16
Mig-21-FM-Identification-Rev. 14 2. Mig-21 bis / iz.75A. General data. The L-17 is assumed to be a Mig-21bis /iz.75A with strengthened airframe. The flight model of the Mig-21bis is built from the one of the Mig-21M. The hypotheses are the following: - Same aerodynamics : CL(Mach ,AoA) and CD(Mach, AoA) laws (we will see later on that this assumption cannot be kept exactly) - Internal fuel capacity set to 2,750 l (2,200 kg / 4,857 lbs @ 0.83 kg/l, but only 2,120 kg / 4,680 lbs usable) - Empty weight set to 6,003 Kg / 13,251 lbs (including pilot and non usable fuel). - Engine changed from Tumanskiy R-11F2SK- 300 to R-25-300 o Military Thrust set to 40.20kN o Full After-Burner set to 69.65kN o Special After-Burner Regime (under 4,000m /13,123 ft) set to 97.20kN Speed limitations: Speed limited to (first reached) - 1,300 km/h (702 Kts) IAS - Mach 2.05 Load factor limitations: Load Factor (Ng) limitation depend on external loads, Mach number and internal fuel weight. They have been defined in reference to the table in appendix. Mach number < 0.8 - Clean or 2 R-3S or R-60 o Fuel < 900 l : 8.5g o Fuel < 4,100 l : 8g - 4 R-3S / R-60 : 7g - External tank(s) : 5g - Rocket pods : 5g - Bombs : 4g Mach number > 0.8 - Clean or 2 R-3S o Fuel < 900 l : 7g o Fuel > 900 l : 6g - 4 R-3S : 6g - External tank(s) : 5g - Rocket pods : 5g - Bombs : 4g Configuration definition. Combat configuration “A” Aircraft loaded with 50% of usable internal fuel, Center Line pylon (but no CL Tank), 2 R- 60 missiles with their pylon and launching rails under external wing stations. - Aircraft (zero usable fuel) : 6,003 kg - 200 gun ammo (Gsh 23) : 95 kg - 1 Center line pylon : 24 kg - 2 Under-wing pylon : 50 kg - Equipped zero usable fuel : 6,172 kg - 50% usable internal fuel : 1,060 kg @0.80 g/cm 3 - Clean Combat Weight : 7,232 kg - 2 APU-60IM rails for R-60 : 70 kg - 2 Missile R-60 : 90 kg - Conf. “A” Combat weight : 7,392 kg This defines a gross weight of 7,392 kg (16,318 lbs) and a Drag Index of 11. Total fuel volume approximated to 1,375l Load factor limitation set to : - 8.0 (mach < 0.8) - 6.0 (mach > 0.8) Combat configuration “B”: Aircraft loaded with 50% of internal fuel, Center Line pylon (but no CL Tank), 2 R-60 missiles with their pylon and launching rails under external wing station, plus two R-13M with their pylon and launching rails under internal wing stations. - Aircraft (zero usable fuel) : 6,003 kg - 200 gun ammo (Gsh 23) : 95 kg Page - 17
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Mig-21-Flight Model - Check six

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