Dittmar HD 153 Motor-Möwe
| HD 153 Motor-Möwe | |
|---|---|
 | |
| HD 153A-1 Motor-Möwe two-seat aircraft at Stuttgart Airport in 1965 | |
| Role | Light civil utility aircraft |
| National origin | West Germany |
| Manufacturer | Dittmar |
| Designer | Heini Dittmar |
| First flight | November 1953 |
| Introduction | 1956 |
| Status | out of service |
| Primary user | private pilot owners and aero clubs |
| Developed from | Dittmar HD 53 Möwe |
The Dittmar HD 153 Motor-Möwe was a West German light aircraft that was first flown in November 1953.
Design and development
The Motor-Möwe, designed by Heini Dittmar who had designed the HD 53 Möwe sailplane, was a motorized development of this sailplane and was initially designed to be powered by engines of 48–63 kW (65–85 hp). The HD 153 prototype was a two-seat side-by-side high wing monoplane powered by a 48 kW (65 hp) Continental A65 engine and was of wooden construction with detachable wing and tail assemblies to facilitate road transportation when needed. A second prototype aircraft was fitted with a 45 kW (60 hp) Hirth engine.[1]
Operational history
The aircraft was designed for private and club use and served as a trainer and glider tug. Heini Dittmar was killed in 1960 when his Motor-Möwe crashed near Essen/Mulheim airport. Small numbers of the type were completed by the end of 1960 and on 1 January 1961 four HD 153 and four HD 156 Motor–Möwen appeared in the West German civil aircraft register.[2] By 1965 four HD 153 and five HD 156 Motor-Möwen were registered in West Germany.[3] By 2007, no examples were known to be active.
Variants
- HD 153
- two-seat aircraft
- HD 153A-1 production two-seaters
- HD 156
- three-seat aircraft fitted with additional side windows
Specifications (HD 153 with A65 engine)
Data from [4]
General characteristics
- Crew: one
- Capacity: one passenger (334 kg (736 lb) payload)
- Length: 6.50 m (21 ft 4 in)
- Wingspan: 11.99 m (39 ft 4 in)
- Height: 1.60 m (5 ft 3 in)
- Wing area: 18.3 m2 (197 sq ft)
- Empty weight: 370 kg (815.5 lb)
- Max takeoff weight: 699 kg (1,542 lb)
- Fuel capacity: 75 l (19.81 US gal; 16.50 imp gal) + optional 200 l (52.83 US gal; 43.99 imp gal) overload tank
- Powerplant: 1 × Continental A65 four-cylinder piston, 48 kW (65 hp)
- Propellers: 2-bladed fixed pitch wooden propeller, 1.798 m (5 ft 10.8 in) diameter
Performance
- Maximum speed: 165 km/h (103 mph; 89 kn)
- Cruising speed: 144 km/h (89 mph; 78 kn)
- Range: 650 km (404 mi; 351 nmi)
- Ferry range: 1,872 km (1,163 mi; 1,011 nmi)
- Endurance: 4.5 hours (13 hours with overload tank)
- Service ceiling: 4,499 m (14,760 ft)
- Time to altitude: 6 minutes to 1,000 m (3,300 ft)
- Fuel consumption: 24 mpg-imp (12 L/100 km; 20 mpg-US)
References
- Gerhard, Peter. World Aviation Register - West Germany 1961 edition. Acton, London: Air-Britain.
- Green and Pollinger, William and Gerald (1955). The Aircraft of the World. London: Macdonald & Co. (Publishers) Ltd.
- Green and Pollinger, William and Gerald (1965). The Aircraft of the World. London: Macdonald & Co. (Publishers) Ltd.
External links
- 28-APR-1960 Heini Dittmars fatal test flight
- 11-APR-1959 wing separated during descent after glider towing