Transcript Document

Mig-21
Flight
Model data
Section A :
Reference
Data
MiG-21MF (‘Fishbed-J’)
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Power Plant
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Fuel capacity:
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One MNPK ‘Soyuz’ (Gavrilov) R-13-300 turbojet rated at 41.53 kN dry and 64.72 kN with afterburning
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:
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Wing: Span 7.15 m; aspect ratio 2.22; area 23.00 m2
Fuselage and tail dimensions:
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Operational weights:
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Empty 5843 kg;
normal take-off 8200 kg with four AAMs;
maximum take-off 9800 kg
Performance:
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Maximum speed:
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Maximum level speed ‘clean’ 2230 km/h or Mach 2.10 at 11000 m
1300 km/h or Mach 1.06 at sea level;
Maximum range:
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Length 15.76 m including probe and
12.25 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
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 11000 m per minute; service ceiling 15250 m
MiG-21MF (‘Fishbed-J’)
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Dimensions
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Weights
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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
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Maximum speed: Mach 2.10 (2230 km/h; 1,385 mph; 1,203 kt) at 11000 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
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Crew: Pilot on a KM-1 zero/150km/h (93 mph or 81 kt) ejector seat
Take-off weight: 9.800 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 107.8 Imp gal) and two 800 littre drop tanks
or three 800 littre (211.3 US gal or 176 Imp gal) drop tanks
Speed
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Wing span: 7.15 meters (23 ft 51 in)
Length: 15.76 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: 23.00 sq meters (247.58 sq ft)
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-13-300 turbojet rated at 9,336 lb (41.53 kN) dry and 6,600 kg (14,550 lb or 64.72 kN) thrust with afterburning,
Provision for RA
Tumansky R-13
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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. R13 is also built under license in China as LM WP13.
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Specifications (R-13-300)
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General characteristics
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Components
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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)
Compressor: Two-spool axial compressor
Performance
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Thrust:
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Specific fuel consumption:
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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)
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-25-300 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-25-300 turbojet rated at 40.26 kN dry and
69.63 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 15.76 m
including probe and 14.70 m excluding probe
MiG-21bis (‘Fishbed-N’)
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Description
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Type: Fighter
Crew: Pilot
First Flight: 1972
Specifications
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Length: 51' 5.5" 15.00 M
Height: 14' 9" 4.5 M
Wignspan: 23' 5.5" 7.15 M
Wingarea: 247.60 Sq Ft 23.00 Sq M
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Empty Weight: 13600 lbs 6050 Kg
Max Weight: 221607lbs 10050 Kg
Propulsion
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Manufacturer: Mikoyan-Gurevich OKB
Designation: Mig-21
Version: BIS
NATO Code: Fishbed-L/N
No. of Engines: 1
Powerplant: Tumansky R-25 turbojet
Thrust (each): 16535 lbs
Performance
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Range: 1118 miles 1800.00 Km
Max Speed: 1250 Mph 2050 Km/H Mmax 2.05
Ceiling: 54500 Ft 16000 M
Tumansky R-25
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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 1975. The engine was also built under license by HAL in India for their fleet of
MiG-21bis.
The R-25-300 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-25-300)
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General characteristics
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Components
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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)
Compressor: Two-spool axial compressor
Performance
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Thrust:
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Specific fuel consumption:
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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)
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
650
On this figure the highest
dark blue curve is supposed
to fit the dashed line of the
MIG-21MF
600
550
500
Excess Specific Power (ft/s)
450
0
5,000
400
10,000
15,000
350
20,000
300
25,000
30,000
250
35,000
40,000
200
150
100
50
0
0.00
0.10
0.20
0.30
0.40
0.50
0.60
0.70
0.80
0.90
1.00
1.10
Mach
1.20
1.30
1.40
1.50
1.60
1.70
1.80
1.90
2.00
2.10
2.20
G forces during a full
sustained turn on alt. 500m,
markings as above
8.00
On this figure the computed
behavior is the dark blue
curve.
Nz (g)
6.00
Pink curve is the “copy” of
the dashed one (Mig-21MF)
one.
Sustained G at Sea Level
4.00
Mig-21 bis Manual (MF data)
2.00
0.00
0.200
0.300
0.400
0.500
0.600
0.700
0.800
Mach
0.900
1.000
1.100
1.200
1.300
Mig-21-MF
Turn Rate Diagram at
15,000 ft
GW = 15,712lbs
Sustained Turn Rate
24.00
On this figure the Pink
Curve (sustained at
15,000ft) is supposed
to fit the Ps=0 curve of
the B&W diagram
20.00
16.00
deg/s
0
10,000
12.00
15,000
20,000
30,000
8.00
4.00
0.00
0.000
0.200
0.400
0.600
0.800
1.000
mach
1.200
1.400
1.600
1.800
2.000
Mig-21 MF
flight Envelope
Energy / Mach Diagram
Drag Index : 0 / 50% Internal Fuel
Full AB
50,000
Alt (ft)
40,000
30,000
0
20,000
100
200
300
10,000
400
500
600
0
0.00
VNE
0.20
0.40
0.60
0.80
1.00
1.20
Mach
1.40
1.60
1.80
2.00
2.20
2.40
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.
750
700
650
600
Excess Specific Power (ft/s)
550
500
450
400
On this figure the highest
dark blue curve is supposed
to fit the solid line of the MIG21bis
350
300
250
200
150
100
50
0
0.00
0.10
0.20
0.30
0.40
0.50
0.60
0.70
0.80
0.90
1.00
1.10
Mach
1.20
1.30
1.40
1.50
1.60
1.70
1.80
1.90
2.00
2.10
2.20
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5,000
10,000
15,000
20,000
25,000
30,000
35,000
40,000
G forces during a full
sustained turn on alt. 500m,
markings as above
10.00
8.00
On this figure the computed
behavior is the dark blue
curve. Sustained G at Sea Level
Nz (g)
6.00
Mig-21 bis Manual (MF data)
Pink curve is the “copy” of
the solid one (Mig-21bis)
4.00
2.00
0.00
0.400
0.500
0.600
0.700
0.800
0.900
Mach
1.000
1.100
1.200
1.300
Mig-21 bis
flight Envelope
Energy / Mach Diagram
Drag Index : 0 / 50% Internal Fuel
Full AB
50,000
Alt (ft)
40,000
30,000
0
20,000
100
200
300
10,000
400
500
600
0
0.00
VNE
0.20
0.40
0.60
0.80
1.00
1.20
Mach
1.40
1.60
1.80
2.00
2.20
2.40