Aero Ae 50
 |
| Ae 50 | |
|---|---|
| General information | |
| Type | Artillery observation post |
| National origin | Czecho-Slovakia |
| Manufacturer | Aero Vodochody |
| Number built | 1 |
| History | |
| First flight | 14 April 1949 |
The Aero Ae 50 was a prototype propeller-driven military reconnaissance aircraft built in Czechoslovakia.
Design and development
[edit]In November 1947, the Czechoslovak Ministry of Defence issued requirements for two light aircraft for service in support of the Czechoslovak Army, a smaller two seat aircraft, to be powered by the 105 hp (78 kW) Walter Minor 4-III engine and a larger aircraft to be powered by the 160 horsepower (120 kW) Walter Minor 6-III engine. The smaller aircraft was intended for artillery spotting, observation and liaison duties. The aircraft was required to provide a good view for the observer and to be able to operate out of small austere airstrips. It needed to have folding wings and be able to be towed behind, or carried on the back of a 2.5te truck. It was also required to be towed by other aircraft, to extend the aircraft's range.[1]
Designed with the artillery spotting role in mind, the Ae 50 was a high-wing monoplane of unusual design, with a fuselage that terminated abruptly immediately aft of the crew cabin, leaving the tailplane to be mounted on a single boom attached to the wing. The tailwheel was mounted at the rear of the fuselage. This arrangement had been intended to maximise the observer's field of view. Another unusual feature was that it incorporated a towing point to allow it to be towed by another, longer-range aircraft to enable it to be transported to a combat zone outside of its range without having to stop and refuel.
First flown on 14 April 1949, it was evaluated against the Praga XE-55 for a defence ministry contract. The Ae 50 was found to have a range of flaws, including directional stability and the operation of the leading-edge slots. These problems were overcome, but the problem of the aircraft being somewhat overweight proved insoluble, and Aero abandoned the development of the aircraft.
Specifications (Ae 50)
[edit]Data from Mongrafie: Aero Ae-50[2]
General characteristics
- Crew: 2
- Length: 7.10 m (23 ft 4 in)
- Wingspan: 10.48 m (34 ft 5 in)
- Height: 2.50 m (8 ft 2 in)
- Wing area: 15.10 m2 (162.5 sq ft)
- Empty weight: 473 kg (1,043 lb)
- Gross weight: 725 kg (1,598 lb)
- Fuel capacity: 75 L (20 US gal; 16 imp gal)
- Powerplant: 1 × Walter Minor 4-III inverted 4-cylinder air-cooled in-line piston engine, 78 kW (105 hp)
Performance
- Maximum speed: 176 km/h (109 mph, 95 kn) (EAS)
- Cruise speed: 150 km/h (93 mph, 81 kn)
- Stall speed: 62 km/h (39 mph, 33 kn)
- Range: 480 km (300 mi, 260 nmi)
- Service ceiling: 4,900 m (16,100 ft)
- Take off distance to 15 m (50 ft): 230 m (755 ft)
- Landing distance from 15 m (50 ft): 190 m (623 ft)
See also
[edit]Aircraft of comparable role, configuration, and era
References
[edit]- ^ Marjánek 1980, p. 712.
- ^ Marjánek 1980, p. 713.
- Marjánek, Pavel (1980). "Mongrafie: Aero Ae-50". Letectví + Kosmonautika (in Czech). Vol. 56, no. 18. pp. 712–714.