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Soko G.2 Galeb

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The first of two prototype SOKO G2-A Galeb (Gull) two-seat trainer and light attack aircraft was flown during May 1961 and production was started in 1963.

Soko G.2 Galeb Article

Powered by a 2,500 lb / 1134kg thrust Rolls-Royce Viper 22-6 turbojet, the G2-A was the standard version for the Yugoslav air force. A G2-AE export variant became available from late 1974 and was built for Libya and Zambia. The basic G2 A version served with the Yugoslav Air Force and G 2A Es with Libya and Zambia.

Production of the G-2A Galeb ended in 1983.

Gallery

G-2A Galeb
Engine: 1 x 2500 lbs.t. (1134 kgp) Bristol Siddeley Viper A.S.V.11 Mk. 22-6 turbojet
Span: 34ft 0.75 in (10.38 m)
Length: 33 ft 11.5 in (10.35 m)
Height: 3.3 m / 11 ft 10 in
Wing area: 209.14 sq.ft (19.43 sq.m)
Empty weight: 5485 lb (2488 kg)
Loaded weight: 7,438 lb. (3374 kg)
Max. speed: 505 mph (812 kph) at 20,340ft (6200 m)
Cruise: 334 mph (537 kph)
Initial climb: 4,500 fpm (22.86 m/sec)
Ceiling: 10000 m / 32800 ft
Range w/max.payload: 1250 km / 777 miles
Crew: 2

SOKO G-2 Galeb

Sud-Est SE 5000 Bardoudeur / SE 5003 Bardoudeur

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A private-venture single-seat tactical support fighter, the SE 5000 Baroudeur – a name derived from the Arabic word baroud for battle, and, in French Foreign Legion parlance, describing a pugnacious fighter – was designed by Wsiewolod J Jakimiuk. Of all-metal construction with a wing sweptback 36 degrees at quarter-chord, the Baroudeur represented an attempt to achieve a measure of independence from permanent runways. In place of a conventional undercarriage, it was provided with a combination of jettisonable take-off trolley and landing skids like the Me 163B Komet.

Sud Est SE 5000 Bardoudeur Article

The first prototype was powered by a 2,395kg SNECMA Atar 101B turbojet and flew on 12 May 1954.

Proposed armament comprised two 30mm or 37mm cannon. The Baroudeur was progressively re-engined with the Atar 101C and 101D-1, this last, rated at 2,600kg, powering a second prototype, which flew on 12 May 1954 and featured a three degree increase in wing anhedral.

Two months earlier, an official contract covered both SE 5000 prototypes as well as three SE 5003 pre-series aircraft. The first SE 5003 was flown in September 1955 with an 3,700kg Atar 101E-4, the second and third aircraft having a 2,850kg Atar 101D-3 and a 3,500kg Atar 101E-3 respectively. The Baroudeur eventually demonstrated the ability to take-off without recourse to the jettisonable trolley and the first SE 5003 was flown with flush-fitting auxiliary fuel tanks on the aft fuselage sides. The NATO nations elected to adopt a more conventional aircraft to meet the lightweight tactical fighter requirement and development of the Baroudeur was discontinued.

SE 5003
Engine: 1 x SNECMA “Atar” 101C, 27.5kN
Loaded weight: 7150 kg / 15763 lb
Empty weight: 4520 kg / 9965 lb
Wingspan: 10.0 m / 33 ft 10 in
Length: 13.66 m / 45 ft 10 in
Height: 3.25 m / 11 ft 8 in
Wing area: 25.30 sq.m / 272.33 sq ft
Max. speed: 1033 km/h / 642 mph
Crew: 1

Sud-Est SE 5000 / SE 5003 Baroudeur

Sud-Est S.E.2415 Grognard II

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A second prototype, the SE.2415 Grognard II, flew in February 1945. A two-seater with wings swept at 32 degrees, it was damaged in a belly landing. Both designs suffered from flutter-induced problems. The definitive production version would have been the SE.2418, which was to have been powered by Rolls-Royce Tay turbojets, but the SO Vautour was selected to meet the Armee de l’Air’s ground-attack requirement instead.

SE.2415-08
Engine: 1 x 2400kg Rolls-Royce Nene 102 turbojet
Max take-off weight: 18000 kg / 39683 lb
Empty weight: 11312 kg / 24939 lb
Wingspan: 13.58 m / 45 ft 7 in
Length: 16.84 m / 55 ft 3 in
Height: 5.20 m / 17 ft 1 in
Wing area: 44.23 sq.m / 476.09 sq ft
Max. speed: 960 km/h / 597 mph
Cruise speed: 880 km/h / 547 mph

Sud-Est S.E.2415 Grognard II

Societe Francaise Deviation Nouvelle SFAN 5

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The two-seat SFAN 5 was a one-off enclosed variant of the earlier SFAN 4, first flying in 1936.

Engine: 1 × Train 4T, 45 kW (60 hp)
Propeller: 2-bladed fixed-pitch pusher
Wingspan: 12.5 m (41 ft 0 in) (10.3 m (34 ft))
Wing area: 18 m2 (190 sq ft) (16.2 m2 (174 sq ft))
Length: 7.05 m (23 ft 2 in)
Empty weight: 285 kg (628 lb)
Gross weight: 500 kg (1,102 lb)
Maximum speed: 115 km/h (71 mph, 62 kn)
Cruise speed: 120 km/h (75 mph, 65 kn)
Landing speed: 45 km/h (28 mph; 24 kn)
Range: 450 km (280 mi, 240 nmi)
Time to altitude: 1,000 m (3,300 ft) in 6 minutes
Wing loading: 30.8 kg/m2 (6.3 lb/sq ft)
Power/mass: 11.17 kg/kW (18.37 lb/hp)
Crew: 2

Societe Francaise Deviation Nouvelle SFAN 2 / SFAN 4

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Licensed for British BAC Drone 1935; modified to suit French requirements as the single seat SFAN 2, powered by a 25 hp Ava engine.

A larger, two-seat side-by-side model to same formula was SFAN 4, powered by a 35 hp Mengin engine. Only two SFAN 4 were built.

It was reported that the French Air Ministry ordered forty Drones from the French company.

The SFAN 5 was a one-off enclosed variant of the earlier SFAN 4.