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EEF Prometheus 1
Entwicklungsgemeinschaft Prometheus 1
Flugzeugbau Der Akademischen Fluggruppe Prometheus 1
 
EEF-Prometheus-1
 
The Prometheus 1 was an experimental powered sailplane from Switzerland, based on the airframe of the FFA Diamant 18.
Design and construction began in late 1970, the wings, Fuselage, tail units and landing gear coming from an original Diamant 18. The aircraft flew for the first time on 21 June 1971, powered by a 176 lb (80 kg) Microturbo Eclair II turbojet engine mounted on a pylon above the wing center-section. This had been later replaced by a more powerful TRS 25 engine.
 
Engine: One 264 lb (120 kg) st Microturbo TRS 25 turbojet
Fuel capacity: 2 x 8.75 Imp gallon (40 litre) wing tanks, 1 x 0.4 Imp gallon (1.8 litre) fuselage tank.
Total fuel: 17.9 Imp gallons (81.8 litres).
Oil capacity: 0.11 Imp gallons (0.5 litres).
Wing span: 59 ft 0.5 in / 18,0 m
Wing aspect ratio: 22,5
Length overall: 24 ft 9.5 in / 7,56 m
Height over tail: 4 ft 5 in / 1,35 m
Tailplane span: 9 ft 6,25 in / 2,90 m
Weight empty: 639 lb / / 290 kg
Max T-O weight: 1,102 lb / / 500 kg
Max level speed / Vne: 146 knots / / 168 mph / / 270 km/h
Max cruising speed at S/L: 113 knots / 130 mph / 210 km/h
Econ cruising speed at SL: 92 knots / 106 mph / 170 km/h
Stalling speed, flaps up: 43.5 knots / 50 mph / 80 km/h
Stalling speed, flaps down: 37 knots / 42.5 mph / 68 km/h
Max rate of climb at S/L: 591 fpm / 180 m/min
Service ceiling: 36,100 ft / 11,000 m
T-O run: 984 ft / 300 m
T-O to 50 ft (15 m): 1,476 ft / 450 m
Landing from 50 ft (15 m): 492 ft / 150 m
Landing run: 164 ft / 50 m
Range with max fuel: > 135 nm / > 155 miles / >250 km
 
 
 
 
 
 
 


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