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Yakolev Yak-25 (I)

yak-25-1


Developed in parallel with the Yak-23, the similarly-powered Yak-25 was conceptually more advanced and derived from the Yak-19. By comparison with the earlier fighter, the Yak-25 employed the higher-speed TsAGI S-9S-9 laminar section at the wing root translating to a KV-4-9 section at the tip with a constant thickness of 9% throughout. Despite the greater diameter of the 1625kg RD-500 (Rolls-Royce Derwent) - similar to that installed in the Yak-23 prototypes - than the RD-10F of the Yak-19, the diameter of the fuselage of the Yak-25 was unchanged. Sweptback horizontal tail surfaces were adopted, provision was made for two 200-litre drop tanks under the wing tips and armament comprised three 23mm NR-23 cannon. The first of two prototypes was flown on 31 October 1947, but, although the subsequent flight test programme was allegedly successful, no production contract was issued for the Yak-25. One of the prototypes was utilised during 1948 for (fixed) tandem-wheel undercarriage trials as part of the Yak-50 development programme.

Max take-off weight: 3235 kg / 7132 lb
Empty weight: 2285 kg / 5038 lb
Wingspan: 8.88 m / 29 ft 2 in
Length: 8.65 m / 28 ft 5 in
Wing area: 14.00 sq.m / 150.69 sq ft
Max. speed: 972 km/h / 604 mph
Range: 1445 km / 898 miles

yak-25-1-ld
Yakolev Yak-25 (I)



 

 


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