Technical data
Type La-VRD
Function fighter
Year 1944
Crew 1
Engines 1*1250kg Lyulka turbojet
Wing Span -
Length -
Height -
Wing Area 15.5m2
Take-off Weight 3,300kg
Payload 910kg
Speed at sea level 890km/h
Landing Speed 140km/h
Ceiling 15000m
Range -
Armament 2*g23mm NS-23 60rpg?

La-VRD, S.A.Lavochkin


In late February, 1944 Captain Engineer V.R.Yefremov, the military representative at OGK (Chief Designer's Department) of the plant #21 informed in his regular report that OGK was designing the La-VRD project powered by Lyulka turbojet rated at 1,250kg of static thrust. The aircraft had to have a twin-boom layout with all-metal one-spar wing with laminar airfoil. The turbojet was to be installed in a fuselage nacell mounted under the wing. The pressurized cockpit was placed in front of the engine, the air intakes were at each side of the fuselage nacell.

The landing gear had a nose wheel retracting behind the armored back of the pilot's seat. Main landing gear legs were retracted backwards in the conjunction of tail booms with the wing. The armament was comprised of two NS-23 cannons installed in forward sections of tail booms. The layout of the aircraft was approved by S.A.Lavochkin and its was agreed with TsAGI (Central Aero/Hydrodynamics Institute).

As was the case with the Gu-VRD, the estimated flight performance was mostly quite achievable. V.R.Yefremov noted only that the problem of acceleration time from idle to full thrust of Lyulka engine had not been solved. Nevertheless the decision to build that aircraft had been made with the goal to hand over the first prototype for flight testing by 1 March, 1946. By 1 November, 1944 the prototype design study had been completed, but because of reasons beyond designers' control neither Gu-VRD, nor La-VRD were built.

The full-scale work on turbojet-powered aircraft in the USSR was delayed for 1.5-2 years.



??? Version with pulse jets : La-138;

Modified October 15, 1996 Back to
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