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Hunting H.126

The Hunting H.126 was an experimental aircraft designed and built by British aviation company Hunting Aircraft.

The aircraft was developed in order to test the performance of blown flaps, which were commonly known in Britain as “jet flaps”, At the time, they were a relatively unknown quantity, thus the Ministry of Aviation issued Specification ER.189D for an appropriate research aircraft to be developed.

During 1959, Hunting Aircraft was selected, being awarded a contract to construct a pair of aircraft.

The first aircraft, serial number XN714, was completed during mid-1962 and initial ground testing commenced during the latter part of the year.

This aircraft performed its maiden flight on 26 March 1963.

Only the single aircraft was ever completed, the second being cancelled mid-construction.

Following the completion of preliminary flights, XN714 was used to conduct a series of one hundred test flights at the Royal Aircraft Establishment’s Aerodynamics Flight at RAE Bedford, the last of which being performed in 1967.

XN714 was transported to the United States during 1969, where it underwent wind tunnel testing by NASA; following its return to the UK, the aircraft was officially withdrawn in 1972.

Presently, the preserved aircraft is on static display at the Royal Air Force Museum Cosford.

The Hunting H.126 is highly unorthodox aircraft; according to Flight, development “posed numerous aerodynamic, thermodynamic and structural problems the ducting of hot gases, large changes of trim which occur with such a large variation in lift coefficient, and the inter-relation between control jets and the conventional elevator and rudder controls”.

Despite this, several aspects of the aircraft, such as its fixed nosewheel undercarriage, were relatively conventional.

There was a deliberate effort to avoid unnecessary complexity, partially as it was felt that testing of the jet flap concept should be carried out in several manageable stages.

The cockpit is situated directly above the engine compartment.

While furnished with oxygen apparatus and a Martin-Baker-built ejection seat, the cockpit was unpressurized.

Due to its use as a test plane, it was outfitted with extensive test instrumentation, much of the rear fuselage space was occupied by the instrumentation, sensors, and recording equipment; in particular, due to heat concerns, extensive temperature monitoring was carried out at various locations across the airframe.

The flight controls, mainly the control column and rudder pedals, operated both the conventional control surfaces and the jet nozzles present in the aircraft’s tail, the latter controlling both pitch and yaw.

The wingtip nozzles, which controlled roll, were operated by an auto-stabilizer system.

The variable-incidence tailplane is hydraulically actuated and was directly linked to the elevators to vary the tail unit’s effective camber.

The ailerons were able to droop, providing a full-span jet flap.

The H.126 was powered by a single Bristol Orpheus turbojet engine. 

All engine thrust was ducted through to a vertical distribution manifold, the top of which featured three ducts on each side leading into the wing to reach a total of eight fishtails, from which exhaust would be directed over the full span of both the flaps and ailerons; one of the wing ducts also supplies the roll-jet nozzle at the wing tip.

The base of the manifold had an additional bifurcated duct that ran aft through either side of the fuselage, providing additional thrust to supplement the fishtails in the wing; these two jet nozzles could be furnished with pilot-controlled spoilers.

A further duct from the manifold supplies the pitch and yaw control nozzles present in the tail unit, as well as another duct for a pitch-trim nozzle.

The extensive ducting necessitated careful insulation and heat-shielding to safely contain the hot gasses; despite this, traditional lightweight alloys were used extensively across the main structure, save for a few critical points.

The fuselage is of conventional stressed-skin construction, the structuring being a mix of longitudinal members and vertical frames, reinforced at key areas such as the wings, undercarriage and engine mounting.

The aircraft’s shoulder-level wing featured a set of struts, not for support but in order to provide piping for the compressed air used in the blown flaps.

The mainplanes used a two-spar construction approach, supported by a single strut and attached via pin-joints to the fuselage; both the wing and strut attachments were designed to facilitate two alternative dihedral angles (4° or 8°).

Each aileron features five hinges, while cooling air was also circulated via slots in the leading and trailing edges; the flaps are of a similar construction.

The two-spar tailplane was pivoted at its rear spar, while four elevator hinges were attached to the rear spar.

The rear control surfaces consisted of a fairly small triangular T-tail, similar to the one on the Gloster Javelin.

The jet flap system consisted of a series of sixteen nozzles arranged along the trailing edge of the wing, which were fed about half of the engine’s hot exhaust gases.

A smaller amount, about 10%, was also fed into small nozzles on the wing tips to provide control thrust at low speeds.

A similar system was later used on the Hawker Siddeley Harrier for similar reasons.

This left little power for forward thrust, and the aircraft was limited to low speeds, but the take-off speed was a mere 32 mph (51 km/h), a speed most light aircraft would have trouble matching.





50 ft 2 in (15.29 m)


45 ft 4 in (13.82 m)


15 ft 6 in (4.72 m)

Wing area

221 sq ft (20.5 m2)


NACA 4424

Empty weight

8,240 lb (3,738 kg)

Max take-off weight

10,740 lb (4,872 kg)


1 × Bristol Siddeley BOr.3 Orpheus Mk.805 turbojet engine,

4,000 lbf (18 kN) thrust


Stall speed

28 kn (32 mph, 52 km/h).


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