Developed in parallel with the Antonov A-11, and making its first flight exactly a week before the latter, the A-13 utilises the same fuselage, undercarriage and tail unit as the A-11 married to a shorter span (39 ft 8.5 in) wing of lower aspect ratio for aerobatic training. This wing is very similar in construction to the A-11's, with a single spar in the root and two spars in the outer wings, and fabric covering aft of the main spar, but flaps are not fitted and the fabriccovered ailerons are not slotted. There are lift spoilers in the upper surfaces. The shorter span wing results in a higher wing loading of 7.07lb/sq ft and a much higher minimum sinking speed of 3.74ft/sec.
Lyulka has producec the small TS-31M turbojet, which weighing only 51 lb (23 kg) and affording a thrust of 121 lb (55 kgp), is used by the Antonov A13 powered glider.
Altogether about 350 examples of the A-11 and A-13 were built.
Span: 39 ft 8.5 in
Length: 19 ft 8.5 in
Wing area: 112.4 sq.ft
Aspect ratio: 13.8
Empty weight: 560 lb
Max take-off weight: 794 lb
Max speed: 217 mph (in smooth air)
Max aero-tow speed: 124 mph
Min sinking speed: 3.74 ft/sec at 60 mph
Best glide ratio: 25:1 at 70 mph
Crew: one pilot
Length: 6.4 m (21 ft 0 in)
Wingspan: 12.1 m (39 ft 8 in)
Height: 1.6 m (5 ft 3 in)
Wing area: 10.4 sq.m (112 sq.ft)
Aspect ratio: 14:1
Empty weight: 270 kg (600 lb)
Gross weight: 360 kg (800 lb)
Maximum speed: 400 km/h (250 mph)
Maximum glide ratio: 25:1
Rate of sink: 1.1 m/s (220 ft/min)