Bisnovat 5

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Bisnovat 5
Role Supersonic research aircraft
National origin USSR
Manufacturer Bisnovat
Designer Matus Bisnovat
First flight 14 July 1948
Number built 2

The Bisnovat 5 (Бисноват 5) was a supersonic research aircraft designed in the USSR in the late 1940s, inspired by the German DFS 346 aircraft that was captured by Soviet troops towards the end of World War II.

The Bisnovat 5 was ordered into development to provide an all-Soviet alternative to an aircraft built with foreign technology. Originally intended to take-off from the ground, gliding flights were carried out from a Petlyakov Pe-8 mothership, similar to the way that the Bell X-1 was dropped from a B-29 Superfortress mothership.

Unpowered flight tests revealed poor stability and dangerous landing characteristics with 5-1,(first prototype), being damaged beyond repair after the third gliding flight. Flight tests with Aircraft 5-2, fitted with a 45 degree swept fin of greater aspect ratio to improve directional stability, resumed on 26 January 1949, but further delays were caused by the pilot landing off the runway causing serious damage. To improve the landing stability 5-2 was modified with wing-tip skids, at the end of downturned wing-tips with 45 degrees anhedral, and a single skid on the centreline, as well as a ventral fin at the rear. Flying and landing qualities were much improved, but progress was slow and the Bisnovat 5 was cancelled without the aircraft making a single powered flight and only sixteen gliding flights, between 14 July 1948 and November 1949, during which a maximum speed of 0.775M was attained.

Specifications (Bisnovat 5)[edit]

Data from Soviet Rocket Fighters[1]

General characteristics

  • Crew: 1
  • Length: 9.92 m (32 ft 7 in) 5-1
11.2 m (37 ft) 5-2 after modifications
  • Wingspan: 6.4 m (21 ft 0 in) 5-1
6.6 m (22 ft) 5-2 with aileron flippers
  • Wing area: 11.315 m2 (121.79 sq ft)
  • Airfoil: root: TsAGI 12045bis; tip: TsAGI P2 (2M)
  • Empty weight: 883 kg (1,947 lb)
  • Gross weight: 3,184 kg (7,020 lb)
  • Powerplant: 1 × Dushkin-Glushko RD-2M3VF twin-chamber liquid-fuelled rocket motor, 19.6 kN (4,410 lbf) thrust above 8,000 m (26,000 ft)


  • Maximum speed: 1,200 km/h (746 mph; 648 kn) design speed
  • Landing speed: 153–160 km/h (95–99 mph; 83–86 kn)
  • Endurance: 2 minutes at full thrust


  1. ^ Gordon, Yefim (2006). Soviet Rocket Fighters. Hinkley: Midland. pp. 118–127.


  • Gordon, Yefim; Bill Gunston (2005). Soviet X-planes. Hinckley: Midland Publishing.
  • Lardier, Christian (1992). L'astronautique soviétique. Paris: A. Colin.
  • Gordon, Yefim (2006). Soviet Rocket Fighters. Hinkley: Midland.
  • Gunston, Bill (1995). The Osprey Encyclopaedia of Russian Aircraft 1875-1995. London: Osprey.
  • Yevtifev, M.D. Ognenny Krylia: Istoriia Sozdannia Reaktivnoi Aviatzii SSSR (1930-1946).

External links[edit]