|Drawing of Su-10 prototype|
|National origin||Soviet Union|
|First flight||Did not fly|
On 26 February 1946 OKB-134 was tasked with developing and building a bomber powered by four Lyul'ka TR-1A or six RD-10 turbojet engines. Work began on 24 April 1946, with many different configurations studied before the design was frozen. Alternative powerplant arrangements were constantly studied and included:-
- 4 x RD-10 (Jumo 004 copies)
- 6 x RD-10 (Jumo 004 copies)
- 4 x Lyul'ka TR-1
- 4 x Lyul'ka TR-1A
- 4 x Lyul'ka TR-2
- 4 x RD-500 (Rolls-Royce Derwent copies)
The Su-10 was a multi-engined jet bomber with a crew of four comprising, Pilot, Navigator/Bomb aimer (usually the Commander of the aircraft), gunner/radio operator, gunner/observer. Ejection seats were provided for Pilot, Navigator and radio Operator, the tail-gunner escaped after jettisoning the tail barbette.
The airframe was of all metal semi-monocoque construction with flush-riveted stressed duralumin skinning and highly stressed parts made from high strength steel. The cantilever shoulder mounted wings were trapezoidal in plan-form with rounded wing-tips. Built in one piece each wing was a two spar structure with ribs and stressed duralumin skinning, using TsAGI Sh-2-12 airfoils at the root and SR-3-12 section at the tip. The tail-unit comprised a 45 degree swept fin and un-swept tailplane at approx 2/3 fin span using TsAGI 1V-00 aerofoil sections. Ailerons and elevators were hydraulically boosted.
Mounted at approx half span the engine nacelles were designed for minimum interference with the wing aerodynamics. The engines were arranged in vertically staggered pairs with the lower engine completely clear of the leading edge exhausting under the wing, whilst the upper engine nacelle carried over the wing exhausting at approx half chord.
Construction of test rigs and a static test fuselage was carried out throughout 1947 and the final propulsion arrangement was settled by a Council of Ministers directive on 11 March 1947, calling for the development and construction of a medium bomber powered by four Lyul'ka TR-1A turbojets. To assist take-off the Su-10 could also use four U-5 JATO boosters fitted on the lower rear fuselage sides.
The first prototype was completed and ready for flight tests when the hammer fell. Under the guise of economising on Research & Development throughout the aviation industry, many small, low output or politically disfavoured OKB's were shut in short order, all work stopping in mid stride. The complete but un-flown Su-10 was given to the Moscow Aviation Institute for use as an instructional airframe.
- Crew: 4 (pilot, navigator, gunner-observer, gunner-radioman)
- Length: 19.55 m (64 ft 2 in)
- Wingspan: 20.6 m (67 ft 6 in)
- Height: 6.56 m (21 ft 6 in)
- Wing area: 71.3 m² (767.4 ft²)
- Empty weight: 13,435 kg (29,620 lb)
- Useful load: 7,700 kg (16,980 lb)
- Max. takeoff weight: 21,140 kg (46,600 lb)
- Powerplant: 4 × Lyulka TR-1A turbojets, 14.7 kN (3,305 lbf) each
- Maximum speed: Mach 0.69 (850 km/h; 530 mph) at altitude
- Range: 1,500 km (930 mi; 810 nmi)
- Service ceiling: 12,000 m (39,370 ft)
- Rate of climb: 12.05 m/s (2371.7 ft/min)
- Wing loading: 297 kg/m² (60.8 lb/ft²)
- Thrust/weight: 0.29
- 5 × 20 mm Berezin B-20E autocannons (1 fixed forward firing in lower forward fuselage, 2 in a remote controlled dorsal barbette and 2 in a KG-2 remote controlled jettison-able tail barbette
- Up to 3,000 kg (6,610 lb) of bombs in the internal bomb bay.
Aircraft of comparable role, configuration and era
- Gordon 2004
- Shavrov 1994
- Gunston 1995