Type P.232/2 Single seat bomber, heavy fighter, low level attack bomber P.232/3 Single seat bomber, heavy fighter, low level attack bomber
Engine 1 Daimler-Benz DB 603G , 1 Junkers Jumo 004C 1 Daimler-Benz DB 603G , 1 Junkers Jumo 004C
Dimensions Length 14,90 m , height  4,50 m,  span 13,80 m , wing area 38,5 m2  , Length 13,80 m , height  5,60 m,  span 13,80 m , wing area 33,5 m2  ,
Weights Empty 5370 kg, loaded  8450 kg, max. take off weight   , fuel 2550 l Empty 5100 kg, loaded  7750 kg, max. take off weight   , fuel 1980 l
Performance Max.. speed  660 km/h at sea level, 805 km/h at 8700 m cruising speed  , range , endurance  , service ceiling  13200 m , climb, take off run 740 m Max.. speed  675 km/h at sea level, 838 km/h at 8700 m cruising speed  , range , endurance  , service ceiling  13300 m , climb, take off run 560 m
Armament 1  30 mm MK 103, 2 20 mm MG 151/20 or 2 MK 103. Bombload 500 kg or 1000 kg
The Dornier P232/2 projcct was initialed in May 1943 as a slngle-seat fast bomber, heavy fighter and low-level attack aircraft. Its overall configuration was derived from the earlier Do 335 ‘Pfeil’ (arrow), nicknamed the Ameisenbär’ (ant-ealer), where the rear reciprocating engine was replaced by a Jumo 004C turbojet which could be attached to the rear fuselage at the standard attachment points. When not in use, the two lateral air intake scoops for the lurbojet could be retracted into the fuselage to reduce drag. The combination of airscrew and turbojct enabled the advantage of both types of propulsion unit to be realised: long ranges when the piston engine was used alone, and a high cruising speed especially at low altitude with both engines in operation. In the latter case, calculations gave a maximum continuous cruising speed of 646km/h - an increase of 85krrvh  over the Do 335, and a range of 1,250km . With the TL engine switched off, range was 3,500km at 530km/h  According to the construction
brochure of 28th May 1943, the tactical capabilities of the P 232/2 at low-level were ideal. Since turbojet installation resulted in reduced weight, the e.xpendable lood could be increased to I000 kg . Fixed armamenl was to consist of a single MK103 firing through the propeller shaft and two MG 151/20 (200rpg) above the engine, replaced later by two MK I08s.
A variant of the P 232/2 was the P 232/3 of September 1943, where the lateral air intakes were replaced by a single intake scoop above the rear fuselage. When only the forward engine was in operation, the intake could be closed by a spring-operated flap to reduce drag. This air intake location, selected in various German projects, was also adopted abroad after the war in civil and military aircraft. Work on Ihe projecl was stopped in late autumn due to the  concentration on the Do 335.