Technical data
Type Gu-VRD
Function fighter
Year 1942
Crew 1
Engines 1500kg Lyulka...? turbojet
Wing Area 11m2
Max.Weight 2,250kg
Speed (sea level) 870km/h (calculated)
Speed (6000 m) 900-1000km/h (calculated)
Climb to 5000m 1.39min
Range 700km
Endurance 1h
Landing Speed 141km/h
Take-off Run 222 m, later considered to be too optimistic
Armament 1*g20mm ShVAK 200rpg
1*mg12.7mm BS 200rpg

Gu-VRD, M.I.Goudkov

In early 1943 when not only there were no captured examples of jet engines and aircraft, but even there was no information at all about German and British turbojet-powered aircraft [in the Soviet Union], the designer M.I.Goudkov has completed a prototype design study of Gu-VRD turbojet-powered fighter.

The project documentation was submitted on 10 March 1943. The Gu-VRD project (see VRD) was reviewed at NII VVS (Scientific Research Institute of the Air Force). A resolution of the leadership of the institute dated 10 April 1943 ordered: "Prepare urgently an evaluation review of the superfast fighter-interceptor of M.I.Goudkov design powered by Lyulka engine".

Department chief I.I.Safronov wrote in his memo of 17 April 1943: "... Apparently, the aircraft would fly with the claimed speed, but the problem is that as of today there is no engine, just the name of its designer. Hence, the emphasis is to be on the engine".

Gu-VRD was a monoplane with the engine placed in the bottom of the fuselage aft of the nose section. The side view of the aircraft had a step behind the engine's nozzle after which the fuselage had a much lesser cross section. Later this layout was named "stepped" and was used in the first Russian jet fighters MiG-9, Yak-15, La-150 and others. Some sources claimed that the stepped layout originated from German design studies of 1944- 1945. It is evident now that the stepped layout appeared in the USSR in 1943 without any foreign influence.

The tipped nose of the aircraft had four segmented air intakes. The wing had trapezoid plane with curved tips. The horizontal and vertical tail design was standard. The retractable landing gear had two main legs and a small tail wheel.

In the meantime Goudkov in his explanatory memo to the project wrote that by that time a combustion chamber of Lyulka engine had been tested, a two-stage axial compressor had been built and tested, achieving 1.25 compression ratio in each stage with 0.75 energy efficiency ratio, both figures rendered quite successful. An engine prototype rated at 750kg of static thrust had been designed and built to 70% readiness. Goudkov noted that the engine itself and majority of Lyulka design team were in Moscow. Lyulka planned to begin developing an engine rated at 1,500kg thrust. The engine had 700kg weight, 0.9m diameter and 2.1m length.

Based on "Samoliotostroyenie v SSSR (1917- 1945)" [Aircraft Development in the USSR], Vol 2, published by TsAGI in 1994. Prepared by Alexander Velovich;
Found at the Russian Aviation Page

Modified October 14, 1996 Back to
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