|National origin||Soviet Union|
The Yakovlev Yak-1000 was a Soviet supersonic technology demonstrator intended to evaluate the aerodynamic layout and field performance of the cropped delta wing discussed in captured German documents in combination with the new Lyulka AL-5 turbojet. The tandem undercarriage proved to be unsatisfactory and there were serious flight stability problems related to the delta wing, enough so that it never flew after an accident during taxiing tests.
A June 1950 Council of Ministers directive ordered Yakovlev to develop a supersonic fighter that used the 50 kN (11,000 lbf) Lyul'ka AL-5 axial compressor turbojet. Based on a recommendation from one of TsAGI aerodynamicists, Yakovlev was directed to use the rhomboid or cropped delta-shaped wing covered in captured German research. The directive was extremely ambitious as it required the maximum speed to be Mach 1.7 at a time when the world speed record was barely over the sound barrier. This requirement had to be revised when the AL-5 was delayed and a substitute engine had to be chosen. No other Soviet turbojet offered the same sort of power as the AL-5 so the project was recast as a technology demonstrator to evaluate the novel wing aerodynamics. The 15.9 kN (3,600 lbf) Klimov RD-500 was chosen and the maximum speed was expected to be 1,100 km/h (680 mph) at a take-off weight of 2,407 kg (5,307 lb).
The Yak-1000 had a circular-section, semi-monocoque fuselage with the engine air intake in the nose. The engine was mounted behind the pressurized cockpit and exhausted through a long tailpipe in the rear fuselage. Two air brakes were fitted on the underside of the rear fuselage. Forward and rear fuel tanks held 430 litres (95 imp gal; 110 US gal) and 167 litres (37 imp gal; 44 US gal) respectively. The entire rear fuselage and tail was removable to allow access to the engine.
The three-spar wings were the most significant new feature on the Yak-1000. Small and rhomboid-shaped, they had an aspect ratio of only 1.46 with 60° leading-edge sweepback with 51°11' sweepback at quarter chord. The thickness/chord ratio was a remarkable 3.4% at the root and 4.5% at the tip. Skin was 1.5mm thick Duralumin. The trailing edge was swept forward 11° and consisted of a full-span flap with inset ailerons.
The delta shaped horizontal stabilizer was set low on the tail and was shaped much like the wing, with 5% thickness. The rudder was tiny, as were the mass-balanced elevators. The tandem "velosipednoye" (bicycle) undercarriage legs, similar to those of the Yak-50, retracted aft, although the forward wheel remained exposed when retracted. Small outrigger struts retracted aft into underwing fairings set at mid-span. On the ground the Yak-1000 had a pronounced nose-high attitude, and the single nose wheel was steerable.
The prototype was completed on 27 February 1951 and it began taxiing trials on 2 March. On the following day it was taxiing at speed up to 250 km/h (160 mph), but was blown off the runway when a strong crosswind caused the aircraft to bank which compressed the strut on the opposite side. This forced the aircraft to veer off the runway when the ailerons proved ineffective at countering the bank and the consequent damage forced the testing to be suspended. Some development was done to try to remedy the problems with instability already revealed, but Yakovlev was unenthusiastic about the whole project and it was cancelled in October 1951.
This decision was considered wise as the peculiar aerodynamics of delta wings would take the Soviets about another five years of experiments to validate in the Mikoyan-Gurevich Ye-4 prototype of the Mikoyan-Gurevich MiG-21 and the Sukhoi T-3 delta-winged aircraft which both first flew in 1955–56.
Had the aircraft met its design expectations it was planned that the aircraft would reach Mach 1.65 (1,750 km/h, 1,087 mph) without afterburner, and Mach 1.88 with afterburner.
Data from Gordon et al., OKB Yakovlev: A History of the Design Bureau and its Aircraft
- Crew: 1
- Length: 11.69 m (38 ft 4 in) excluding nose probe
- Wingspan: 4.59 m (15 ft 1 in)
- Max takeoff weight: 2,407 kg (5,307 lb)
- Fuel capacity: 597 litres (131 imp gal; 158 US gal)
- Powerplant: 1 × Klimov RD-500 centrifugal-compressor turbojet, 15.9 kN (3,600 lbf) thrust
- Maximum speed: 1,100 km/h (684 mph; 594 kn)
- Aircraft of comparable role, configuration and era
- Gordon, pp. 184–85
- "Speed Record Club". Retrieved 2009-11-10.
- Gordon, pp. 185, 187
- Gunston 1995, p. 482
- Gunston, 1997
- Gordon, p. 187
|Wikimedia Commons has media related to Yakovlev aircraft.|
- Gordon, Yefim; Komissariov, Dmitry and Sergey (2005). OKB Yakovlev: A History of the Design Bureau and its Aircraft. Hinckley, England: Midland Publishing. ISBN 1-85780-203-9.
- Gunston, Bill (1995). The Osprey Encyclopedia of Russian Aircraft 1875-1995. London: Osprey. ISBN 1-85532-405-9.
- Gunston, Bill. Yakovlev Aircraft since 1924. London, UK: Putnam Aeronautical Books, 1997. ISBN 1-55750-978-6.