Home IAR 93

IAR 93

E-mail Print

INCAS - IAR 93
SOKO /VTJ - J - ORAO

imag1

Single - seat  version  of  the  Romanian  Air Force's,    IAR-93B

1.  TYPE :

Single-seat close support, ground attack and tactical reconnaissance aircraft, with  for secondary capability as low level interceptor. Combat capable two-seat version used also for advanced flying and weapon training.

2. PROGRAMS:


Joint design by Romania (INCAS) and Yogoslavian (VTJ) engineers, started in 1970  under original project name YUROM, to meet requirements of both air forces; two single-seat prototypes started in each country 1972, making simultaneous first flights 31 october 1974: first flight in each country of a two-seat prototype 23 January 1977; each manufacturer then built 15 pre-production aircraft (first flight 1978);  series production began in Romania  (IAv Craiova, now Avioane) 1979, in Yugoslavia (SOKO) 1980.

3.  CURRENT VERSIONS:


IAR-93A: Romanian single and two-seat versions with no-afterburning Viper Mk  632-41 turbojets; first flight 1981; production completed.

IAR-93B: Romanian single and two-seat versions with afterburning Viper Mk 633-47 turbojets; first flight 1985.

4. CUSTOMERS:


Romanian Air Force (26 single-seat and 10 two-seat IAR-93A, all delivered, and 165 IAR-93B);

DESIGN FEATURES:

Wing of  NACA 65A-008 (modified) section, shoulder-mounted with 0° incidence and 3° 30' anhedral from roots; sweepback  35° at quarter-chord and approx 43°on outer leading-edges; incidence 0°;  inboard leading-edges extended forward (except on prototypes / pre-production) at 65° sweepback; small boundary layer fence on upper surface of each outer panel; fuselage has hydraulically actuated airbrake underneath on each side forward of mainwheel bay, dorsal spine fairing, per-nib fairing, pen-nib fairing above exhaust nozzles, and detachable rear portion for access to engine bays; all-sweptback tail surfaces, plus strake beneath rear fuselage each side.
imge2
For exploded view click here

STRUCTURE:

Conventionally built, almost entirely of aluminium alloy, except for honeycomb rudder and tailplane on later production aircraft; two-spar wings  with ribs, stringers and partially machined skin; wing spar box forms integral fuel tanks on production aircraft; pre-series aircraft have rubber fuel cells, forward of which sandwich panels.


LANDING GEAR:


Hydraulically retractable tricycle type of  INCAS design, with single-wheel hydraulically steerable nose unit, twin-wheel main units. All units retract forward into fuselage. Two-stage AEROSTAR   hydro/nitrogen shock absorber in each unit. Mainwheels and tubeless types size 615 x 225 mm;  pressure 4,5 bars (65,3 lb/sq in). Nosewheel and tubeless tyres size 450 x 190 mm, pressure 4,0 bars (58,0 lb/sq in). on all afterburning versions. Hydraulic disc brakes on each mainwheel unit, and electronic anti-skid system. Min ground turning radius 7,00 m (22 ft 11½ in). Bullet fairing at base of rudder contains hydraulically  4,2m (13 ft  9½ in) diameter braking parachute.

FLYING CONTROLS:
Internally balanced plain ailerons, single-slotted trailing-edge flaps, two-segment leading-edge slats (three-segment on prototype/pre-production aircraft), low-set all-moving tailplane and inset rudder, all hydraulically actuated (except leading-edge slats: electrohydraulic), with AEROTECH servo-actuators for primary control surfaces; no aileron or rudder tabs.

imge3
For exploded view click here

SYSTEMS:


Bootstrap type environmental control system for cockpit pressurisation (max differential 0,214 bar ; 3,1 lb/sq in), air-conditioning, and windscreen de-icing/demisting. Two AEROSTAR / Prva Petoletka independent hydraulic systems, each of 207 bars (3000 lb/sq in) pressure, flaw rate 48 litres/min (12,7 US gallons/min; 10,6 Imp gallons/min), for actions of leading-edge slats, trailing-edge flaps, ailerons, tailplane, rudder, airbrakes, landing gear extension/retraction, mainwheel brakes, nosewheel steering, brake-chute and afterburner nozzles. Backup system for landing gear, wheel brakes and primary flight controls. No pneumatic system. Main electrical system is 28 V DC, supplied by two Lucas BC - 0107, 9 kW engine driven starter/generators through two voltage regulators and a switching system, and a 24 V 36Ah nickel-cadmium battery ; four 300VA static inverters for 115 V AC power at 400 Hz. High pressure (150 bars; 2,175 lb/sq in) gaseous oxygen system for crew. Planned retrofit of air intake and wing leading-edge de-icing.

imge4

For exploded view click here

imge5
For exploded view click here
EQUIPMENT:

Landing light under nose, forward of nosewheel bay; taxying light on nosewheel shock strut.
imge6
For exploded view click here
AVIONICS:

Standard avionics include VHF/UHF air-to-air and air-to-ground com.radio (20W transmission power); gyro unit (Honeywell SGP500 twin-gyro platform in ORAO), radio altimeter, ADF, radio compass and marker receiver; IFF (Romanian IAR-93B aircraft only); and GEC-MARCONI three-axis stability augmentation system, incorporating a basic bank / altitude hold autopilot and emergency wings-level facility.
imge7
For exploded view click here
ARMAMENT (IAR-93A/B):

Two 23 mm GSh-23L twin-barrel cannon in lower front fuselage, below engine air intakes, with 200 rds/gun. Gun camera and GEC-Marconi D282 gyro gunsight. Fire external stores station, of which inboard underwing pair and fuselage centerline station are each stressed for loads up to 500 kg (1,102 lb); outboard underwing stations stressed for up to 300 kg (661 lb) each, giving max external stores load of 1,500 kg (3,307 lb). Typical weapon loads can include two or three 500 kg bombs; four or five 250 kg bombs; four multiple carriers each with three 100 kg bombs; two such multiple carriers plus two L-57-16MD launchers each with 16´ 57 mm rockets; four L-57-16MD launchers; four launchers each with two 122 mm, one 128 mm or one 240 mm rockets; a GSh-23L cannon pad with four L-57-16MD rockets launchers; four 160 kg KPT-150 or similar munition dispensers; or four L-57-32 launchers each with 32´ 57 mm rockets. Some IAR-93Bs equipped to carry up eight air-to-air missiles, on twin launch rails, on four underwing station. Centreline and inboard underwing points can carry drop tanks.

imge8

For exploded view click here

EXTERNAL    STORES MASS kg ( lb )

external_93

imge9

POWER PLANT (non-afterburning version):


Two 17,79 KN (4,000 lb st) Turbomecanica/Orao (license built Rolls-Royce) Viper Mk 632-41 turbojets, mounted side by side in rear fuselage; air intake on each side of fuselage, below cockpit canopy. Pre-series aircraft have seven fuselage tanks and two collector tanks, with combined capacity of 2,480 litres (655 US gallons; 545,5 Imp gallons), and two 235 litre (62 US gallons; 51,75 Imp gallons) rubber fuel cells in wings, giving total internal fuel capacity of 2,950 litres (779 US gallons; 649 Imp. gallons). Provision for carrying three 500 litre (132 US gallons; 110 Imp. gallons) auxiliary fuel tanks, one on underfuselage stores attachment and one inboard under each wing. Pressure refuelling points in fuselage below starboard air intake; gravity refueling points in fuselage near starboard wing trailing-edge and in each external tank. Oil capacity 6,25 litres (1,65 US gallons: 1.37 Imp gallons).

POWER PLANT (afterburning version):

Two Turbomecanica/Orao (license build Rolls-Royce) Viper Mk 633-47 turbojets, each rated at 17,79 kN (4,000 lb st) dry and 22,24 kN (5000 lb st) with afterburning. Production aircraft have fire fuselage tanks and two collector tanks, plus two integral wing tanks, giving total internal capacity of 3,120 litres (842 US gallons; 686 Imp gallons). Drop tanks, refuelling points and oil capacity as for non-afterburning version.

ACCOMMODATION:


Single-seat or tandem two-seat cockpit(s), with Martin-Baker zero/zero seat for each occupant (RU10J in IAR-93, Y-10LB in ORAO), capable of ejection throught canopy. Canopy of single-seat IAR-93A and J-22 hinged at rear and actuated electrically to open upward; single-seat IAR-93B, and all two-seaters, have manually operated canopies opening sideways to starboard. All accommodation pressurised, heated and air-conditioned. Dual controls in two-seat versions.

General Data


DIMENSIONS EXTERNAL:
Wing span 9.30 m (30 ft 6¼ in)
Wing chord at root 4.20 m (13 ft 9 3/8 in)
at tip 1.40 m (4 ft 7½ in
Wing aspect ratio 3,33
Length overall, incl probe:
single-seater 14.90 m (48 ft 10½ in)
two-seater 15.38 m (50 ft 5½ in)
Lenhth of fuselage:
single-seater 13,02 m (42 ft 8½ in)
two-seater 14,44 m (47 ft 4½ in)
Fuselage: Max width 1,62 m (5 ft 3¾ in)
Height overall 4,52 m (14ft 10 in)
Tailplane span 4,59 m (15 ft 0¼ in)
Wheel track (c/l of shock struts) 2,50 m (8 ft 2½ in)
Wheelbase single-seater 5,40 m (17 ft 8½ in)
two-seater 5,88 m (19 ft 3½ in)
AREAS:
Wings, gross 26,00 m2 (279,86 sq ft)
Ailerons (total) 2,39 m2 (25,73 sq ft)
Trailing-edge flaps (total) 3,33 m2 (35,84 sq ft)
Leading-edge slats (total) 2,22 m2 (23,90 sq ft)
Fin 3,55 m2 (38,21 sq ft)
Rudder 0,88 m2 (9,47 sq ft)
Tailplane 7,31 m2 (78,68 sq ft)
WEIGHTS AND LOADINGS:
Weights empty, equipped    IAR-93A 6,150 kg (13,558 lb)
IAR-93B 5,750 kg (12,676 lb)
Max internal fuel : IAR-93A 2,457 kg (5,416 lb)
IAR-93B 2,400 kg (5,291 lb)
Max external load: IAR-93A 1,500 kg (3,307 lb)
IAR-93B 2,500 kg (5,511 lb)
Normal T-O weight clean: IAR-93A 8,826 kg (19,458 lb)
IAR-93B 8,400 kg (18,519 lb)
Max T-O weight IAR-93A 10,326 kg (22,765 lb)
IAR-93B 10,900 kg (22,030 lb)
Max landing weight: IAR-93A 8,826 kg (19,458 lb)
IAR-93B 9,360 kg (20,635 lb)
Max wing loading: IAR-93A 397,1 kg/m2 (81,3 lb/sq ft)
IAR-93B 419,2 kg/m2 (85,9 lb/sq ft)

Max power loading: IAR-93A 289,8 kg/kN (2,84 lb/lb st)
IAR-93B 245,2 kg/kN (2,40 lb/lb st)
PERFORMANCE: (IAR-93A at max T-O weight, IAR-93B at 8,400 k)
Normal T-O weight clean:  IAR-93A 8,826 kg (19,458 lb)
Max level speed at S/L:


IAR-93A

577 knots (1,070 km/h; 665 mph)

IAR-93B

586 knots (1,086 km/h; 675 mph)

Max cruising speed :

IAR-93A at 7,000 m (22,965 ft)

394 knots (730 km/h; 453 mph)

IAR-93B at 5,000 m (15,240 ft)

587 knots (1,089 km/h; 676 mph)

Stalling speed at S/L:

IAR-93A

130 knots (241 km/h; 150 mph)

IAR-93B

148 knots (274 km/h; 171 mph)

Max rate of climb at S/L:

IAR-93A 2,040 m (6,693 ft)/min

IAR-93B

3,900 m (12,800 ft)/min

Service ceiling: IAR-93A

10,500 m (34,450 ft)

IAR-93B

13,600 m (44,625 ft)

T-O run: IAR-93A

1,500 m (4,921 ft)

IAR-93B

800 m (2,625 ft)

T-O to 15 m (50 ft): IAR-93A

1,600 m (5,249 ft)

IAR-93B

1,150 m (3,775 ft)
Landing from 15 m (50 ft):   IAR-93A 1,650 m (5,413 ft)

IAR-93B

1,520 m (4,987 ft)

IAR-93B with brake-chute

990 m (3,250 ft)

Landing run: IAR-93A

720 m (2,362 ft)

IAR-93B

1,050 m (3,445 ft)

IAR-93B with brake-chute

690 m (2,265 ft)

Landing run with brake-chute:

IAR-93A, IAR-93B:

670 m (2,200 ft)

Tactical radius, IAR-93A, IAR-93B:

lo-lo-lo with four rocket launchers, 5 min over target

140 nm (260 km; 161 miles)

hi-hi-hi patrol with three 500 litre drop tanks, 45 min over target

205 nm (380 km; 236 miles)

lo-lo-hi with two rocket launchers, six 100 kg bombs and one 500 litre drop tank, 10 min over target

243 nm (450 km; 280 miles)

hi-hi-hi with four 250 kg bombs and one 500 litre drop tank, 5 min over target

286 nm (530 km; 329 miles)

g  limits: IAR-93A, IAR-93B

+8/-4,2

imge10

Single-seat J-22 Orao close support/ground attack aircraft , with additional side view (top) of two-seat NJ-22 (Jane's /Dennis Punnett)

For more information, contact: Email: This e-mail address is being protected from spambots. You need JavaScript enabled to view it





 

1.  TYPE :


Single-seat close support, ground attack and tactical reconnaissance aircraft, with  for secondary capability as low level interceptor. Combat capable two-seat version used also for advanced flying and weapon training.

2. PROGRAMS:


Joint design by Romania (INCAS) and Yogoslavian (VTJ) engineers, started in 1970  under original project name YUROM, to meet requirements of both air forces; two single-seat prototypes started in each country 1972, making simultaneous first flights 31 october 1974: first flight in each country of a two-seat prototype 23 January 1977; each manufacturer then built 15 pre-production aircraft (first flight 1978);  series production began in Romania  (IAv Craiova, now Avioane) 1979, in Yugoslavia (SOKO) 1980.

3.  CURRENT VERSIONS:


IAR-93A: Romanian single and two-seat versions with no-afterburning Viper Mk  632-41 turbojets; first flight 1981; production completed.

IAR-93B: Romanian single and two-seat versions with afterburning Viper Mk 633-47 turbojets; first flight 1985.

4. CUSTOMERS:


Romanian Air Force (26 single-seat and 10 two-seat IAR-93A, all delivered, and 165 IAR-93B);


DESIGN FEATURES:

Wing of  NACA 65A-008 (modified) section, shoulder-mounted with 0° incidence and 3° 30' anhedral from roots; sweepback  35° at quarter-chord and approx 43°on outer leading-edges; incidence 0°;  inboard leading-edges extended forward (except on prototypes / pre-production) at 65° sweepback; small boundary layer fence on upper surface of each outer panel; fuselage has hydraulically actuated airbrake underneath on each side forward of mainwheel bay, dorsal spine fairing, per-nib fairing, pen-nib fairing above exhaust nozzles, and detachable rear portion for access to engine bays; all-sweptback tail surfaces, plus strake beneath rear fuselage each side.

For exploded view click here


STRUCTURE:


Conventionally built, almost entirely of aluminium alloy, except for honeycomb rudder and tailplane on later production aircraft; two-spar wings  with ribs, stringers and partially machined skin; wing spar box forms integral fuel tanks on production aircraft; pre-series aircraft have rubber fuel cells, forward of which sandwich panels.


LANDING GEAR:



Hydraulically retractable tricycle type of  INCAS design, with single-wheel hydraulically steerable nose unit, twin-wheel main units. All units retract forward into fuselage. Two-stage AEROSTAR   hydro/nitrogen shock absorber in each unit. Mainwheels and tubeless types size 615 x 225 mm;  pressure 4,5 bars (65,3 lb/sq in). Nosewheel and tubeless tyres size 450 x 190 mm, pressure 4,0 bars (58,0 lb/sq in). on all afterburning versions. Hydraulic disc brakes on each mainwheel unit, and electronic anti-skid system. Min ground turning radius 7,00 m (22 ft 11½ in). Bullet fairing at base of rudder contains hydraulically  4,2m (13 ft  9½ in) diameter braking parachute.

FLYING CONTROLS:

Internally balanced plain ailerons, single-slotted trailing-edge flaps, two-segment leading-edge slats (three-segment on prototype/pre-production aircraft), low-set all-moving tailplane and inset rudder, all hydraulically actuated (except leading-edge slats: electrohydraulic), with AEROTECH servo-actuators for primary control surfaces; no aileron or rudder tabs.



For exploded view click here


SYSTEMS:



Bootstrap type environmental control system for cockpit pressurisation (max differential 0,214 bar ; 3,1 lb/sq in), air-conditioning, and windscreen de-icing/demisting. Two AEROSTAR / Prva Petoletka independent hydraulic systems, each of 207 bars (3000 lb/sq in) pressure, flaw rate 48 litres/min (12,7 US gallons/min; 10,6 Imp gallons/min), for actions of leading-edge slats, trailing-edge flaps, ailerons, tailplane, rudder, airbrakes, landing gear extension/retraction, mainwheel brakes, nosewheel steering, brake-chute and afterburner nozzles. Backup system for landing gear, wheel brakes and primary flight controls. No pneumatic system. Main electrical system is 28 V DC, supplied by two Lucas BC - 0107, 9 kW engine driven starter/generators through two voltage regulators and a switching system, and a 24 V 36Ah nickel-cadmium battery ; four 300VA static inverters for 115 V AC power at 400 Hz. High pressure (150 bars; 2,175 lb/sq in) gaseous oxygen system for crew. Planned retrofit of air intake and wing leading-edge de-icing.

For exploded view click here

For exploded view click here

EQUIPMENT:

Landing light under nose, forward of nosewheel bay; taxying light on nosewheel shock strut.

For exploded view click here

AVIONICS:

Standard avionics include VHF/UHF air-to-air and air-to-ground com.radio (20W transmission power); gyro unit (Honeywell SGP500 twin-gyro platform in ORAO), radio altimeter, ADF, radio compass and marker receiver; IFF (Romanian IAR-93B aircraft only); and GEC-MARCONI three-axis stability augmentation system, incorporating a basic bank / altitude hold autopilot and emergency wings-level facility.

For exploded view click here

ARMAMENT (IAR-93A/B):

Two 23 mm GSh-23L twin-barrel cannon in lower front fuselage, below engine air intakes, with 200 rds/gun. Gun camera and GEC-Marconi D282 gyro gunsight. Fire external stores station, of which inboard underwing pair and fuselage centerline station are each stressed for loads up to 500 kg (1,102 lb); outboard underwing stations stressed for up to 300 kg (661 lb) each, giving max external stores load of 1,500 kg (3,307 lb). Typical weapon loads can include two or three 500 kg bombs; four or five 250 kg bombs; four multiple carriers each with three 100 kg bombs; two such multiple carriers plus two L-57-16MD launchers each with 16´ 57 mm rockets; four L-57-16MD launchers; four launchers each with two 122 mm, one 128 mm or one 240 mm rockets; a GSh-23L cannon pad with four L-57-16MD rockets launchers; four 160 kg KPT-150 or similar munition dispensers; or four L-57-32 launchers each with 32´ 57 mm rockets. Some IAR-93Bs equipped to carry up eight air-to-air missiles, on twin launch rails, on four underwing station. Centreline and inboard underwing points can carry drop tanks.


For exploded view click here

EXTERNAL    STORES MASS kg ( lb )

5 x BM - 500 BOMBS 2500 ( 5512 )
4 x LMB 2 x 250 BOMB RACKS
8 x BEM - 250 BOMBS
1 x BM - 500 BOMB
2660 ( 5864 )
2 x LMB 3 x 100 BOMB RACKS
6 x BE - 100 BOMBS
2 x LMB 2 x 250 BOMB RACKS
4 x BEM - 250 BOMBS
1 x  DROP TANK
2205 ( 4861 )
4 x LMB 4 x 100 BOMB RACKS
16 x BE - 100 BOMBS
1 x DROP TANK
2285 ( 5038 )
4 x LMB 3 x 100 BOMB RACKS
12 x BE - 100 BOMBS
1 x DROP TANK
1805 ( 3979 )
4 x GA ADAPTORS
8 x LPR 57 - 16 ROCKET LAUNCHERS
1 x DROP TANK
1645 ( 3627 )
4 x LPR 57 - 32 ROCKET LAUNCHERS
1 x DROP TANK
1405 ( 3097 )
4 x LPR - 122 ROCKET LAUNCHERS
8 x PRIND -122 ROCKETS
1 x DROP TANK
1145 ( 2524 )
2 x GA ADAPTORS
4 x LPR 57 - 16 ROCKET
3 x DROP TANKS
1935 ( 4266 )





POWER PLANT (non-afterburning version):



Two 17,79 KN (4,000 lb st) Turbomecanica/Orao (license built Rolls-Royce) Viper Mk 632-41 turbojets, mounted side by side in rear fuselage; air intake on each side of fuselage, below cockpit canopy. Pre-series aircraft have seven fuselage tanks and two collector tanks, with combined capacity of 2,480 litres (655 US gallons; 545,5 Imp gallons), and two 235 litre (62 US gallons; 51,75 Imp gallons) rubber fuel cells in wings, giving total internal fuel capacity of 2,950 litres (779 US gallons; 649 Imp. gallons). Provision for carrying three 500 litre (132 US gallons; 110 Imp. gallons) auxiliary fuel tanks, one on underfuselage stores attachment and one inboard under each wing. Pressure refuelling points in fuselage below starboard air intake; gravity refueling points in fuselage near starboard wing trailing-edge and in each external tank. Oil capacity 6,25 litres (1,65 US gallons: 1.37 Imp gallons).

POWER PLANT (afterburning version):



Two Turbomecanica/Orao (license build Rolls-Royce) Viper Mk 633-47 turbojets, each rated at 17,79 kN (4,000 lb st) dry and 22,24 kN (5000 lb st) with afterburning. Production aircraft have fire fuselage tanks and two collector tanks, plus two integral wing tanks, giving total internal capacity of 3,120 litres (842 US gallons; 686 Imp gallons). Drop tanks, refuelling points and oil capacity as for non-afterburning version.


ACCOMMODATION:



Single-seat or tandem two-seat cockpit(s), with Martin-Baker zero/zero seat for each occupant (RU10J in IAR-93, Y-10LB in ORAO), capable of ejection throught canopy. Canopy of single-seat IAR-93A and J-22 hinged at rear and actuated electrically to open upward; single-seat IAR-93B, and all two-seaters, have manually operated canopies opening sideways to starboard. All accommodation pressurised, heated and air-conditioned. Dual controls in two-seat versions.

 

General Data


DIMENSIONS EXTERNAL:
Wing span 9.30 m (30 ft 6¼ in)
Wing chord at root 4.20 m (13 ft 9 3/8 in)
at tip 1.40 m (4 ft 7½ in
Wing aspect ratio 3,33
Length overall, incl probe:
single-seater 14.90 m (48 ft 10½ in)
two-seater 15.38 m (50 ft 5½ in)
Lenhth of fuselage:
single-seater 13,02 m (42 ft 8½ in)
two-seater 14,44 m (47 ft 4½ in)
Fuselage: Max width 1,62 m (5 ft 3¾ in)
Height overall 4,52 m (14ft 10 in)
Tailplane span 4,59 m (15 ft 0¼ in)
Wheel track (c/l of shock struts) 2,50 m (8 ft 2½ in)
Wheelbase single-seater 5,40 m (17 ft 8½ in)
two-seater 5,88 m (19 ft 3½ in)
AREAS:
Wings, gross 26,00 m2 (279,86 sq ft)
Ailerons (total) 2,39 m2 (25,73 sq ft)
Trailing-edge flaps (total) 3,33 m2 (35,84 sq ft)
Leading-edge slats (total) 2,22 m2 (23,90 sq ft)
Fin 3,55 m2 (38,21 sq ft)
Rudder 0,88 m2 (9,47 sq ft)
Tailplane 7,31 m2 (78,68 sq ft)
WEIGHTS AND LOADINGS:
Weights empty, equipped    IAR-93A 6,150 kg (13,558 lb)
IAR-93B 5,750 kg (12,676 lb)
Max internal fuel : IAR-93A 2,457 kg (5,416 lb)
IAR-93B 2,400 kg (5,291 lb)
Max external load: IAR-93A 1,500 kg (3,307 lb)
IAR-93B 2,500 kg (5,511 lb)
Normal T-O weight clean: IAR-93A 8,826 kg (19,458 lb)
IAR-93B 8,400 kg (18,519 lb)
Max T-O weight IAR-93A 10,326 kg (22,765 lb)
IAR-93B 10,900 kg (22,030 lb)
Max landing weight: IAR-93A 8,826 kg (19,458 lb)
IAR-93B 9,360 kg (20,635 lb)
Max wing loading: IAR-93A 397,1 kg/m2 (81,3 lb/sq ft)
IAR-93B 419,2 kg/m2 (85,9 lb/sq ft)

Max power loading: IAR-93A 289,8 kg/kN (2,84 lb/lb st)
IAR-93B 245,2 kg/kN (2,40 lb/lb st)
PERFORMANCE: (IAR-93A at max T-O weight, IAR-93B at 8,400 k)
Normal T-O weight clean:  IAR-93A 8,826 kg (19,458 lb)
Max level speed at S/L:


IAR-93A

577 knots (1,070 km/h; 665 mph)

IAR-93B

586 knots (1,086 km/h; 675 mph)

Max cruising speed :

IAR-93A at 7,000 m (22,965 ft)

394 knots (730 km/h; 453 mph)

IAR-93B at 5,000 m (15,240 ft)

587 knots (1,089 km/h; 676 mph)

Stalling speed at S/L:

IAR-93A

130 knots (241 km/h; 150 mph)

IAR-93B

148 knots (274 km/h; 171 mph)

Max rate of climb at S/L:

IAR-93A 2,040 m (6,693 ft)/min

IAR-93B

3,900 m (12,800 ft)/min

Service ceiling: IAR-93A

10,500 m (34,450 ft)

IAR-93B

13,600 m (44,625 ft)

T-O run: IAR-93A

1,500 m (4,921 ft)

IAR-93B

800 m (2,625 ft)

T-O to 15 m (50 ft): IAR-93A

1,600 m (5,249 ft)

IAR-93B

1,150 m (3,775 ft)
Landing from 15 m (50 ft):   IAR-93A 1,650 m (5,413 ft)

IAR-93B

1,520 m (4,987 ft)

IAR-93B with brake-chute

990 m (3,250 ft)

Landing run: IAR-93A

720 m (2,362 ft)

IAR-93B

1,050 m (3,445 ft)

IAR-93B with brake-chute

690 m (2,265 ft)

Landing run with brake-chute:

IAR-93A, IAR-93B:

670 m (2,200 ft)

Tactical radius, IAR-93A, IAR-93B:

lo-lo-lo with four rocket launchers, 5 min over target

140 nm (260 km; 161 miles)

hi-hi-hi patrol with three 500 litre drop tanks, 45 min over target

205 nm (380 km; 236 miles)

lo-lo-hi with two rocket launchers, six 100 kg bombs and one 500 litre drop tank, 10 min over target

243 nm (450 km; 280 miles)

hi-hi-hi with four 250 kg bombs and one 500 litre drop tank, 5 min over target

286 nm (530 km; 329 miles)

g  limits: IAR-93A, IAR-93B

+8/-4,2

Single-seat J-22 Orao close support/ground attack aircraft , with additional side view (top) of two-seat NJ-22 (Jane's /Dennis Punnett)

For more information, contact:

Email: This e-mail address is being protected from spambots. You need JavaScript enabled to view it

 

Who's Online

We have 530 guests online

Links

Featured Links:
http://www.edu.ro :: Ministerul Educatiei Nationale
Ministerul Educatiei Nationale
Bir birimize Bursa'da herzaman Kaliteye sahib cikmaliyiz hangi Bransta olur iseniz olunuz iyi islerde guven verdirmemizde gerekir Bursa Eskort Bulma kalitesi ile herzaman ust siralarda Queen gibi olmasi tesaduf degil. bakiyoruz genelde pacoz kadinlar oluyor normal modellerde bu pacozlarin yaninda kala kala onlara benziyorlar gercekten en guzel ve kaliteli olanlari secip burada paylasiyoruz.\n\nEskort olarak is yapiyorlar ama Serseri gibiler her daim bakimli ve seksi bir gorunuse sahip olmaya sizleri ve bizleri herzaman en ust seviyede memnun etmeyi hedefliyorlar.
Escort bayanlarından en guzelleride burada bulacaksiniz
http://www.research.gov.ro/ :: MCI
Ministerul Cercetarii şi Inovarii
UEFISCDI
Unitatea Executiva pentru Finantarea Invatamantului Superior, a Cercetarii, Dezvoltarii si Inovarii
ANELIS PLUS
“Acces național electronic la literatura științifică și de cercetare”