Presentation on theme: "Mig-21 Flight Model data. Section A : Reference Data."— Presentation transcript:
Mig-21 Flight Model data
Section A : Reference Data
MiG-21MF (‘Fishbed-J’) Power Plant –One MNPK ‘Soyuz’ (Gavrilov) R turbojet rated at kN dry and kN with afterburning Fuel capacity: –Internal fuel 2076 kg comprising 2600 liters of which only 1800 liters are usable within low-speed center of gravity limits; –external fuel up to one 490 liter and two 800 liter or three 800 liter drop tank; no provision for inflight refueling Dimensions: –Wing: Span 7.15 m; aspect ratio 2.22; area m2 –Fuselage and tail dimensions: Length m including probe and m excluding probe and inlet centerbody; height 4.50 m; tailplane span 3.74 m; wheel track 2,78 m; wheel base 4.71 m Operational weights: –Empty 5843 kg; –normal take-off 8200 kg with four AAMs; –maximum take-off 9800 kg Performance: –Maximum speed: Maximum level speed ‘clean’ 2230 km/h or Mach 2.10 at m 1300 km/h or Mach 1.06 at sea level; Maximum range: –Ferry range 1800 km with three drop tanks; –radius 370 km on a hi-lo-hi attack mission with four 250 kg bombs, –or 740 km on a hi-lo-hi attack mission with two 250 kg bombs and one drop tank Maximum rate of climb at sea level m per minute; service ceiling m
MiG-21MF (‘Fishbed-J’) Dimensions –Wing span: 7.15 meters (23 ft 51 in) –Length: meters (51 ft 81 in) with probe –12.25 meters (40 ft 2.3 in) excluding probe and inlet centerbody –Height: 4.50 meters (14 ft 9 in) –Wing area: sq meters ( sq ft) Weights –Crew: Pilot on a KM-1 zero/150km/h (93 mph or 81 kt) ejector seat –Take-off weight: kg (21,600 lb) –Weapon load: 1500 kg (3,307 lb) –Internal fuel load: 2076 kg (4,576 lb) –External fuel load: one 490 littre (129.4 US gal or Imp gal) and two 800 littre drop tanks –or three 800 littre (211.3 US gal or 176 Imp gal) drop tanks Speed –Maximum speed: Mach 2.10 (2230 km/h; 1,385 mph; 1,203 kt) at meters (36,090 ft) –Mach 1.06 (1300 km/h; 807 mph; 702 kt) at sea level –Cruising speed: km/h ( mph or kt) at 5000 meters (16,405 ft) Range –Maximum range: 1,100 km (684 miles) without auxiliary fuel tanks –Ferry range 1800 km (1,118 miles or 971 nm) with three drop tanks –Radius 370 km (230 miles or 200 nm) on a hi-lo-hi attack mission with four 250 kg (551 lb) bombs –Radius 740 km (460 miles or 400 nm) on a hi-lo-hi attack mission with two 250 kg (551 lb) bombs and drop tanks Ceiling –Ceiling: 15,250 meters (50,035 ft) –Rate of climb: 11,000 meters (36,090 ft) per minute at sea level G limit: -4 to +8 Radar: None Targeting: Ferranti ISIS D-126R gyro sight Engine: One Tumansky R turbojet rated at 9,336 lb (41.53 kN) dry and 6,600 kg (14,550 lb or kN) thrust with afterburning, Provision for RA
Tumansky R-13 The Tumansky R-13 is a development of the successful Tumansky R-11 engine. It is a two-spool axial-flow turbojet featuring a new 5-stage high-pressure compressor, new combustion chamber design to facilitate restarting the engine at high altitudes, new afterburner, and greater use of titanium components. It is used by MiG-21M, MF, SM, and SMT, and Sukhoi Su-15M and TM. R- 13 is also built under license in China as LM WP13. Specifications (R ) –General characteristics Type: Afterburning turbojet Length: 4,605 mm (181.3 in) Diameter: 1,095 mm (43.1 in) Dry weight: 1,205 kg (2,656 lb) –Components Compressor: Two-spool axial compressor Performance –Thrust: 39.9 kN (8,970 lbf) military thrust 63.7 kN (14,320 lbf) with afterburner Overall pressure ratio: 8.9:1 Turbine inlet temperature: 1,005 °C (1,840 °F) –Specific fuel consumption: 95 kg/(h·kN) (0.93 lb/(h·lbf)) at idle 213 kg/(h·kN) (2.09 lb/(h·lbf)) with afterburner –Thrust-to-weight ratio: 52.8 N/kg (5.4:1)
MiG-21bis (‘Fishbed-N’) The Mig-21bis used the Tumansky R engine whilst the MF used the Tumansky R-13. Built in 1972, this is the initial third- generation development of the MiG-21 series with the MNPK ‘Soyuz (Tumanski) R turbojet rated at kN dry and kN with afterburning in a re- engineered airframe which provides greater strenght at reduced weight. Other changes include –updated avionics –further enlarged dorsal fairing to allow an increase to 2900 liters of internal fuel that can can be supplemented by up to one 800 liter and two 490 liter or three 490 liter drop tanks. –In other respect, the MiG-21bis differs from the MiG-21MF in its maximum disposable warload of 1500 kg, and length of m including probe and m excluding probe
MiG-21bis (‘Fishbed-N’) Description –Manufacturer: Mikoyan-Gurevich OKB –Designation: Mig-21 –Version: BIS –NATO Code: Fishbed-L/N Type: Fighter Crew: Pilot First Flight: 1972 Specifications –Length: 51' 5.5" M –Height: 14' 9" 4.5 M –Wignspan: 23' 5.5" 7.15 M –Wingarea: Sq Ft Sq M –Empty Weight: lbs 6050 Kg –Max Weight: lbs Kg Propulsion –No. of Engines: 1 –Powerplant: Tumansky R-25 turbojet –Thrust (each): lbs Performance –Range: 1118 miles Km –Max Speed: 1250 Mph 2050 Km/H Mmax 2.05 –Ceiling: Ft M
Tumansky R-25 The Tumansky R-25 was designed as a replacement for Tumansky R-13 in MiG-21 fighters. R-25 is a two-spool axial-flow turbojet featuring a new compressor with increased overall pressure ratio and airflow, variable afterburner, and greater use of titanium. The engine was used on MiG-21bis and Sukhoi Su-15bis. A total of 3,200 R-25 were built between 1971 and The engine was also built under license by HAL in India for their fleet of MiG-21bis. The R engine (4020/6960 daN thrust) can be put in a "second afterburning" stage when speed is Ma>1 and altitude less than 4000m. For 3 minutes max it gives 9720 daN (other source 9708 daN) of thrust. Than it requires at least another 3 minutes of cooling. Specifications (R ) –General characteristics Type: Afterburning turbojet Length: 4,615 mm (181.7 in) Diameter: 1,191 mm (46.9 in) Dry weight: 1,212 kg (2,670 lb) Components –Compressor: Two-spool axial compressor Performance –Thrust: 40.3 kN (9,060 lbf) military power 68.5 kN (15,400 lbf) with afterburner Overall pressure ratio: 9.5:1 Turbine inlet temperature: 1,040 °C (1,904 °F) –Specific fuel consumption: 93 kg/(h·kN) (0.91 lb/(h·lbf)) at idle 98 kg/(h·kN) (0.96 lb/(h·lbf)) at maximum military power 229 kg/(h·kN) (2.25 lb/(h·lbf)) with afterburner –Thrust-to-weight ratio: 56.5 N/kg (5.8:1)
Climb rate from alt. 500m. Solid line is MiG-21bis, dashed is MiG-21MF The bis is in a "special engine regime", like a second afterburning stage, the MF is afterburning.
G forces during a full sustained turn on alt. 500m, markings as above
Mig-21-MF Turn Rate Diagram at 15,000 ft GW = 15,712lbs Curve are Iso-Ps The “0” curve describes the sustained turn rate
Halfloop (immelman) path (viewed from the side), starting altitude 100m, starting velocity 1100km/h line on the left - 6G, line on the right - 3G solid - 21bis on special regime dashed - 21MF/Mirage-IIIC (do they have such similar flight envelopes?) on full afterburners.
instantaneous turn path (viewed from above) at alt. 500m solid line MiG-21bis dashed MiG-21MF Mirage-IIIC
Section B: Mig-21 MF Flight Model Mapping
Climb rate from alt. 500m. Dashed is MiG-21MF On this figure the highest dark blue curve is supposed to fit the dashed line of the MIG-21MF
G forces during a full sustained turn on alt. 500m, markings as above On this figure the computed behavior is the dark blue curve. Pink curve is the “copy” of the dashed one (Mig-21MF) one.
Mig-21-MF Turn Rate Diagram at 15,000 ft GW = 15,712lbs On this figure the Pink Curve (sustained at 15,000ft) is supposed to fit the Ps=0 curve of the B&W diagram
Mig-21 MF flight Envelope
Section C : Mig-21 bis Flight Model Mapping
Climb rate from alt. 500m. Solid line is MiG-21bis, dashed is MiG-21MF The bis is in a "special engine regime", like a second afterburning stage, the MF is afterburning. On this figure the highest dark blue curve is supposed to fit the solid line of the MIG- 21bis
G forces during a full sustained turn on alt. 500m, markings as above On this figure the computed behavior is the dark blue curve. Pink curve is the “copy” of the solid one (Mig-21bis)