Yakovlev Yak-30 (1948)

Yakovlev Yak-30

Company type	Experimental jet interceptor
Industry	Aerospace
Founded	1948
Headquarters	Soviet Union
Products	Jet interceptor aircraft

This article is about the interceptor of the 1940s. For the trainer from the 1960s, see Yakovlev Yak-30 (1960).

The Yakovlev Yak-30 was a Soviet experimental jet interceptor developed in the late 1940s. It originated from the Yak-25, primarily distinguished by its wings swept back at a 35° angle measured at the quarter chord. The design preserved the fuselage, tail assembly, and landing gear of its predecessor.

History

The Yak-30 was created to fulfill a Soviet demand for a fighter capable of reaching Mach 0.9 speeds and operating from unprepared airfields. Achieving this performance necessitated a wing design with significant sweepback. Yakovlev adapted the existing Yak-25 experimental fighter by integrating a wing with a 35-degree sweep.

Development

The Yak-30 closely resembled the earlier Yak-25, undergoing only minimal modifications. It retained the Yak-25’s fuselage, albeit reshaped to a circular cross-section. The tail configuration remained similar but featured an enlarged horizontal stabilizer and a single-piece rudder. Armament continued to consist of three NR-23 cannons, and the cockpit arrangement remained consistent. Wingtip fuel tanks were eliminated due to adverse effects on the center of gravity; instead, redesigned tanks were mounted flush beneath the wing, positioned midway between the fuselage and wingtips. Propulsion was provided by an RD-500 turbojet engine delivering 1,590 kgf (3,505 lbf) of thrust.

Testing

The initial prototype, bearing callsign "42" and rudder number "5," undertook its maiden flight on 4 September 1948 with pilot Anokhin at the controls, who continued test flights until mid-December that year.

A second prototype, designated Yak-30D and introduced into flight testing in early 1949, featured several enhancements: a 38 cm (15 in) fuselage extension aft of the cockpit; redesigned main landing gear doors that formed part of the external fuselage skin; Fowler flaps replacing split flaps; increased capacities for fuel and ammunition; updated oxygen supply systems and radio equipment; and air brakes installed on the rear fuselage. These modifications raised the normal loaded weight (excluding external fuel) by approximately 110 kg (243 lb).

During trials, the aircraft achieved Mach 0.935 in a dive. Relative to the Yak-25, it demonstrated an increase in maximum speed by roughly 40 km/h (25 mph) and gained an additional service ceiling of about 1,000 m (3,281 ft). Nevertheless, pilots reported inadequate control effectiveness from the swept wings’ ailerons.

Despite improvements introduced with the Yak-30D addressing many deficiencies found in the initial prototype, production of the more advanced MiG-15 had already commenced by this time. Consequently, evaluations conducted by NII V-VS became largely theoretical in nature. The Yak-30 designation was subsequently reassigned to a different aircraft developed in 1960, known as the Yakovlev Yak-30 (1960).

Specifications (Yak-30)

File:Yak-30.gif

Bibliography

• Gunston, Bill. Yakovlev Aircraft since 1924. London: Putnam Aeronautical Books, 1997. ISBN 1-55750-978-6.