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Dittmar HD 153 Mowe
RAAB Mora
Pützer Motorraab/Moraa
 HD 153A-1 Motor-Möwe
The Motor-Möwe, designed by Heini Dittmar who had designed the Dittmar 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). Heini Dittmar, the designer, was well known before the war as an international Gliding champion.
The fuselage is of wood, plywood covered, with the rear top decking detachable. An entrance door on the left side gives access to the two side-by-side seats, one of which comes out if an extra tank is fitted. Baggage room is at rear of cabin. Dual control is fitted. The wooden wing has a one-piece spar with torsion-box plywood leading edge, and lift spoilers on the top surfaces. The tail unit is of similar construction, the balanced rudder being fabric covered. Spring tabs are fitted to the elevators. A fixed spatted tricycle undercarriage has nose-wheel steering direct from a hand lever in the cabin.
Preparations for road-towing are simplicity itself; two bolts are withdrawn to release the tail controls, the wing, rudder and tailplane are stowed on top of the fuselage and bolted down, and a dolly with ball coupling is attached to the undercarriage.
The aircraft was designed for private and club use and served as a trainer and glider tug.
Heini Dittmar, the aircraft’s designer, was killed in 1960 when his Motor-Möwe crashed near Essen/Mulheim airport.
The prototype, D-EBEF, first flight was in November 1953
A second prototype aircraft was fitted with a 45 kW (60 hp) Hirth engine. The second Motor Gull (D-EHYT differs from prototype (D-EBEF) by having redesigned fin/rudder and more windows.
 second prototype
Production HD 153 two-seat aircraft were designated HD 153A-1.
 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. In 1965 four HD 153 and five HD 156 Motor-Möwen were registered in West Germany. By 2007, no examples were known to be active.
 The RAAB Mora was a two-seat powered version of the Doppelraab (Reihe 6).
 RAAB Mora
 Built as Doppelraab VII glider, the Raab Doppelraab Hankur 1 D-KKKK was rebuilt as a motor glider.
RAAB Mora
Engine: VW 25 hp
Wingspan: 13.64 m
Wing area: 19.00 sq.m
Length: 6.80 m
Height: 1.60 m
Empty weight: 350 kg
MTOW: 550 kg
Wing loading: 29 kg/sq.m
Power loading: 23 kg/hp
Cruise: 120 kph
Landing speed: 45 kph
T/O run: 200 m
ROC: 1.5 m/sec
Range: 1000 km
Seats: 2
HD 153 Motor-Move
Powerplant: one 65-h.p. Continental
Propellor diameter 5.9 ft
Wingspan: 39 ft 4 in
Wing area 197 sq ft
Length: 21 ft 4 in
Height: 5 ft 3 in
Empty weight: 2151 lb
MTOW: 1,542 lb
Load: 736 lb
Top speed: 102.3 m.p.h.
Cruising speed: 89.5 m.p.h.
Landing speed: 37.2 m.p.h.
Climb to 3,280 ft: 7 min
Fuel capacity: 16.5 Imp gallons
Endurance: 4.5 hours
Opt extra fuel: 44 Imp gallon
Endurance opt/fuel: 13 hours
Fuel Consumption 24 m.p.g.
Accommodation: two.
Powerplant: 85-h.p. Continental
Propellor diameter 5.9 ft
Wingspan: 39 ft 4 in
Wing area 197 sq ft
Length: 21 ft 4 in
Height: 5 ft 3 in
Empty weight: 2151 lb
MTOW: 1,542 lb
Load: 736 lb
Top speed: 124 m.p.h
Cruising speed: 105.4 m.p.h
Landing speed: 37.2 m.p.h.
Climb to 3,280 ft: 7 min
Fuel capacity: 16.5 Imp gallons
Endurance: 4.5 hours
Opt extra fuel: 44 Imp gallon
Endurance opt/fuel: 13 hours
Fuel Consumption 24 m.p.g.
Accommodation: two.
Powerplant: 1 × Continental C90-12F, 67 kW (90 hp)
Propeller: 2-bladed Hoffman "HoCo" fixed pitch wooden
Wingspan: 12 m (39 ft 4 in)
Wing area: 18.3 m2 (197 sq ft)
Aspect ratio: 8.5
Airfoil: Göttingen 367 modified
Length: 6.5 m (21 ft 4 in)
Height: 2.1 m (6 ft 11 in)
Empty weight: 465 kg (1,025 lb) equipped
Gross weight: 760 kg (1,676 lb)
Fuel capacity: 140 l (36.98 US gal; 30.80 imp gal) in two wing tanks
Optional fuel: 200 l (52.83 US gal; 43.99 imp gal) overload tank
Maximum speed: 170 km/h (110 mph, 92 kn)
Cruise speed: 150 km/h (93 mph, 81 kn)
Landing speed: 65 km/h (40 mph; 35 kn)
Range: 1,000 km (620 mi, 540 nmi)
Ferry range: 1,872 km (1,163 mi, 1,011 nmi)
Endurance: 4.5 hours (13 hours with overload tank)
Service ceiling: 4,500 m (14,800 ft)
Time to altitude: 1,000 m (3,300 ft) in 6 minutes
Take-off run: 150 m (492 ft)
Landing run: 130 m (427 ft)
Crew: one
Capacity: one passenger (334 kg (736 lb) payload)
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