adsH said:LOL we all know that russians were no good in R&D at that time russians even after absorbing all the R&D and scientist couldn't produce capable engines for there migs we (UK had to give them those) the only two countries that had serious R&D at that time for modern WarFare equipments were undoubtedly Germany and UK.
1. Let's not include the US (e.g. Manhattan project)?!?!?
2. The key operant words being "at that time" > my point exactly
3. for your information:
Source: Krylya Rodiny [Wings of the Motherland, a Russian monthly for aviation fans]
Issue 3 (782), March 1996, p30-31
Author: Vladimir Perov
Title: Not Copying Germans. The first indigenous projects of turbojet-powered aircraft [in the USSR]
[Abstracts]
In early 1943 when not only there was no captured examples of
jet engines and aircrfat, but even there was no information at
all about German and British turbojet-powered aircraft [in the
Soviet Union], the designer M.I.Gudkov has completed a prototype
design study of Gu-VRD turbojet-powered fighter.
The project documentation was submitted on 10 March 1943.
Gudkov was one of the designers of LaGG-1 and LaGG-3 fighters,
he developed and launched series production of the LaGG-3
variant with 37mm ShK-37 gun firing through the propeller
shaft. The aircraft had provisional designation K-37. In 1941
Gudkov was the first to have designed and built the LaGG-3
variant named Gu-82 with M-82 air-cooled engine. By that time
the Gu-1 fighter resembling Aircobra was approaching its
completion. Gudkov also designed LaG-5 modifications powered
by M-71 air-cooled engine and DM-30 diesel.
The Gu-VRD project [VRD = vozdushno-reactivny dvigatel, the
Russian for turbojet] 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 Gudkov's design powered by Lyulka's
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".
In the meantime Gudkov in his explanatory memo to the project
wrote that by that time a combustion chamber of Lyulka's 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. Gudkov noted that
the engine itself and majority of Lyulka's design team were in
Moscow. Lyulka planned to begin developing an engine rated at
1,500kg thrust.
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 planform with curved tips. The
horisontal and vertical tail design was standard. The
retractable landing gear had two main legs and a small tail
wheel. The aircraft take-off weight was estimated at 2,250kg,
including 400kg of fuel. The engine had 700kg weight, 0.9m
diametre and 2.1m length. The wing area was relatively small -
11.0 sq.m.
The aircraft's armament was to be mounted in the upper section
of the nose and was comprised of one ShVAK 20mm cannon with 200
rounds and one BS high-calibre [12.7mm] machine gun, also with 200
rounds. The static thrust of the engine was assumed to be
1,500kg. Gudkov's calculations estimated maximum speed at
870km/h at sea level and 900-1,000km/h at 6,000m altitude. Time
to climb to 5,000m was estimated at 1.39 min. Range at 80%
maximum speed - up to 700km, endurance - about 1 hour. The
take-off run was estimated at 222m, a rather overoptimistic
forecast as the future experience with first turbojet-powered
aircraft showed. Landing speed was estimated at 141km/h.
On 9 April, 1943 Gudkov sent a letter to NII VVS informing the
Air Force that he was completing a project of a high-speed
bomber powered by two Lyulka's turbojets rated at 1,500kg
static thrust. The aircraft's flight weight was to be 6,500kg
with the crew of three, maximum speed 780-800km/h at 6,000m,
1,200-1,500km range , 1,200-1,500kg bomb load. The armament
would be comprised of one cannon and one BS machine gun.
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 Lyullka's turbojet
rated at 1,250 kg 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 nacelle
mounted under the wing. The pressurised cockpit was placed in
front of the engine, the air intakes were at each side of the
fuselage nacelle.
The landing gear had a nose wheel retracting behind the
armoured 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 with total 120 rounds. The take-
off weight was to be 3,300kg including 910kg of payload. Wing
area - 15.5 sq.m, aspect ratio - 5.85. The layout of the
aircraft was approved by S.A.Lavochkin and its was agreed with
TsAGI (Central Aero/Hydrodynamics Institute).
The estimated flight performance was as follows: maximum sea
level speed 890km/h, service ceiling 15,000m, landing speed
140km/h. 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's 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 wide-scale work on
turbojet-powered aircraft in the USSR was delayed for 1.5-2
years.