The Gyöngyös 33 was the first Hungarian designed sailplane and was named after its place and year of manufacture. It was designed by Zoltán Janka and built in the MOVERO (Aviation Section of Hungarian National Defence Association) workshops at Gyöngyös. His design target was to produce an aircraft that would out-perform the 1928 RRG Professor.

It was an all wood monoplane with a two-part wing built around a forward main spar and a rear false spar. The inner area of each part was rectangular in plan, tapering strongly outboard. The leading edges ahead of the main spar were plywood-covered, as was the whole wing at the inner-outer junction; the rest was fabric-covered. An aileron filled the whole trailing edge of each outer section. The two parts joined at a narrow centre-section on a raised fuselage pylon and were braced on each side with a V-strut from the fuselage bottom to the wing spars at the inner-outer junctions.

The Gyöngyös 33’s six-sided fuselage was formed by a wooden frame and was plywood-covered. The pilot had an open cockpit ahead of the wing leading edge with the wing pylon immediately behind him. A rubber-sprung landing skid below him ran from the nose almost to the trailing edge. The fuselage tapered rearwards to a cantilever empennage. The fin was small and ply-covered with a tall rudder which, like the all-moving tailplane apart from its leading edge, was fabric covered.

The first flight took place on 11 June 1933. A fortnight later the Gyöngyös 33 slope-soared for 5 h 43 m, gaining 1,140 m (3,740 ft) of altitude, a Hungarian record. On 27 June it set a national duration record of 10 h 7 m. In 1934 it made a 64 km (40 mi; 35 nmi) flight.

The Gyöngyös 33 is now on display in the Hungarian Technical and Transportation Museum, Budapest.

Length: 7.37 m (24 ft 2 in)
Wingspan: 18.55 m (60 ft 10 in)
Wing area: 19.3 sq.m (208 sq ft)
Aspect ratio: 17.8
Airfoil: Göttingen 549
Empty weight: 179 kg (395 lb)
Gross weight: 250 kg (551 lb)
Maximum glide ratio: >20 at 55 km/h (34 mph; 30 kn)
Rate of sink: 0.6 m/s (120 ft/min) minimum

In the late 1930s, more modern gliders with improved aerodynamics were developed in various Soviet cities, designed to set new competition records. Among these models was the JAI-9 (Russian: ХАИ-9) single-seat monoplane glider designed by AV Kovalenko built by JHA students in 1937.

The JAI-9 wing presented a cantilever configuration with high aspect. In the JAI-9, for the first time, the TsAGI flaps were installed. It is worth noting the JAI-9 high wing loading.

The pilot was located in a cockpit closed by a transparent cover, which barely protruded in the contours of the glider’s fuselage.

The tests showed that the JAI-9 flew well and was easy to control in the air.

The tailless experimental glider known as “Biezlonzherokka JAI” or “Stringerless Glider” (Russian: ХАИ Безлонжеронка) was designed and built under the direction of Professor Serguei Ivanovich Kuzmin at the Kharkov Aviation Institute (JAI) in 1934. Its development was with the collaboration of engineers AA Lazariev and Ye. S. Balinski.

The Stringerless Glider was designed in a tailless flying wing composition with fluted wings with empennage at the ends. The entire construction was made of wood.

The wing stood out for the marked aspect of 13. The center plane was characterized by a structure of four spars on which the cabin was located.

The removable consoles featured a remarkable dihedral and specific wing profile. As a distinctive detail of the project, it is worth highlighting the total absence of a stringer in the construction of these consoles, which was reflected in the name of the glider. These sections were built using a honeycomb structure with an outer covering around stringers. The lightened wing veins served as the basis for the thin covering layer. The wing consoles were fixed by means of duralumin pieces to the steel supports fixed to the spars of the center plane. This construction method would be the basis for the further development of modern three-layer structures.

The extreme empennages consisted of a fixed keel and rudders. The control of the apparatus was achieved by means of double-section mobile elements covering a large part of the span (60%). The outer section of the ailerons was capable of turning upward at a greater angle than the inner, thereby achieving increased control at large angles of attack.

The glider control system in the center plane was rigid and in the wing by ropes. When installing the consoles to the center plane, the control of the surfaces of these sections was automatically connected.

The glider featured an open cockpit for the pilot, located above the small centerplane, which ended with a tall fairing headrest.

The JHA project without stringers was completed in March 1933. Its construction was started at the Kharkov Aviation Factory with the direct participation of KA Kalinin. Later the works were transferred to the JAI workshops with the participation of KA Kalinin, IG Nieman and S. Ya. Zholkovski. In June the glider was successfully tested in the institute’s laboratories.

The JHA without spars first flew the 14 September of 1934. The tests, developed by the pilot VD Kozulya, showed excellent stability. The sparless JHA was able to hold the course with the stick free and could execute various manoeuvres.

Wingspan: 13 m
Length: 3.2 m
Height: 1.5 m
Empty weight: 160 kg