Soko J-20 Kraguj: Difference between revisions
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The '''Soko J-20 Kraguj''' (''Sparrowhawk'') is a light military, single-engine, low-wing single-seat aircraft with a metal airframe, capable of performing [[close air support]], [[ |
The '''Soko J-20 Kraguj''' (''Sparrowhawk'') is a light military, single-engine, low-wing single-seat aircraft with a metal airframe, capable of performing [[close air support]], [[counterinsurgency]] (COIN), and [[aerial reconnaissance|reconnaissance]] missions, that was designed by [[Aeronautical Technical Institute|VTI]] and manufactured by [[SOKO]] of Yugoslavia, first flown in 1962. |
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==Design== |
==Design== |
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Revision as of 22:44, 1 June 2021
 | This article includes a list of general references, but it lacks sufficient corresponding inline citations. (February 2013) |
| J-20 Kraguj | |
|---|---|
| |
| J-20 Kraguj in private collection with Yugoslav marks at a local airshow in Serbia, 2009. | |
| Role | COIN |
| Manufacturer | SOKO |
| Design group | Aeronautical Technical Institute |
| First flight | 21 November 1962 |
| Introduction | 1964 |
| Status | Retired in 1989 |
| Primary user | Yugoslav Air Force (1967-1989) |
| Produced | 1964-1977 |
| Number built | 43 |
The Soko J-20 Kraguj (Sparrowhawk) is a light military, single-engine, low-wing single-seat aircraft with a metal airframe, capable of performing close air support, counterinsurgency (COIN), and reconnaissance missions, that was designed by VTI and manufactured by SOKO of Yugoslavia, first flown in 1962.
Design
It is of classic semi-monocoque, metal structure with a slightly tapered wing. The pilot is accommodated in an enclosed, heated and ventilated cockpit with adjustable seats. The cockpit canopy slides backwards to open. The landing gear is non-retractable with a tail wheel. Rubber dampers provide shock absorption, and hydraulic brakes are used for wheel braking.
The power plant comprises one 340 hp Textron Lycoming GSO-480-B1J6 piston engine and Hartzell HC-B3Z20-1/10151C-5 three-blade metal variable-pitch propeller. The engine cooling airflow is intensified by means of two specially designed ejectors. 36 US Gal of fuel contained in two rubber tanks enables a flight range of 350 NM for the fully armed configuration of the aircraft. 28 V DC electric power is supplied from a 1,5 kW generator and a storage battery. De-fogging and de-icing of the windshield is done by blowing of hot air.
Armament
Permanent armament comprises two wing-mounted 7.7 mm Colt–Browning Mk-II machine guns with 650 rounds each and a collimator sight in the cockpit. For combat missions there is a capacity for an external load of bombs and two 57 mm and two 128 mm (HVAR-5) air-to-ground rocket launchers. Adapters on the underwing pylons can be used to switch the armament configuration from free-fall bombs to multi-tube launchers with twelve 57 mm air-to-ground rockets. Cluster or cargo bombs, or 128 mm air-to-ground rockets can be fitted.
Operation
The aircraft was specially designed for low-altitude missions against day and night visible ground targets in a broad area. It was readily available to be loaded with weapons and supplied through a flexible system of auxiliary airfields that required no special preparations, especially in mountainous regions. Yugoslav military planners assumed that potential aggressor will first disable airfields. Therefore, J-20 Kraguj was designed to take-off from short unprepared runways, even ones covered in deep snow when fitted with skis. It was also called a "Partisan aircraft".[citation needed]
The Kraguj P-2 was intended for close ground force support, and could be used for training of pilots in visual day/night flights, aiming, missile firing and bombing of ground targets.
Operators
- Croatian Air Force - Former operator.
- Republika Srpska Air Force - Former operator.
Specifications (J-20)
Data from Jane's All the World's Aircraft 1969-70 [1]
General characteristics
- Crew: 1
- Length: 7.93 m (26 ft 0 in)
- Wingspan: 10.64 m (34 ft 11 in)
- Height: 3.00 m (9 ft 10 in)
- Wing area: 17.0 m2 (183 sq ft)
- Aspect ratio: 6:1
- Airfoil: NACA 4415
- Empty weight: 1,130 kg (2,491 lb)
- Max takeoff weight: 1,624 kg (3,580 lb)
- Fuel capacity: 240 L (53 imp gal; 63 US gal)
- Powerplant: 1 × Lycoming GSO-480-B1A6 6-cylinder air-cooled horizontally-opposed piston engine, 250 kW (340 hp)
- Propellers: 3-bladed Hartzell HC-B3Z20-1 constant-speed propeller, 2.44 m (8 ft 0 in) diameter
Performance
- Maximum speed: 295 km/h (183 mph, 159 kn) at 1,500 m (4,900 ft)
- Cruise speed: 280 km/h (170 mph, 150 kn) at 1,500 m (4,900 ft)
- Stall speed: 88 km/h (55 mph, 48 kn) (flaps down)
- Range: 800 km (500 mi, 430 nmi)
- Rate of climb: 8.00 m/s (1,575 ft/min)
- Take-off run to 15 m (50 ft): 189 m (620 ft)
- Landing run from 15 m (50 ft):: 324 m (1,063 ft)
Armament
- Guns: 2 × 7.7 mm Colt–Browning Mk.II machine guns (650 rounds each)
- Rockets: 2 × 12 round rocket pack or 6 × 57 mm or 127 mm rocket
- Bombs: 2 × 100 kg (220 lb) bombs
See also
Aircraft of comparable role, configuration, and era
References
- ^ J W R Taylor 1969, p.506.
- Taylor,John W.R. (editor). Jane's All The World's Aircraft 1969-70. London: Sampson Low,1969.
External links
