| Type | High speed bomber project, 2-3 seat |
| Engine | 2 BMW 109-028 turboprops |
| Dimensions | Length 28,00 m , height 6,50 m , span 32,50 m , wing area , prop. diameter 4,10 m |
| Weights | Empty , loaded 78800 kg , max. take off weight |
| Performance | Max.. speed 870 km/h , cruising speed km/h , range 2800 km, endurance , service ceiling m , climb |
| Armament | Bombload 2000 kg |
Designed in 1943 by the BMW project department headed by Flugbaumeister Dipl-lng Kappus.
Two BMW 109-028 turboprop engines, each with a shaft output of 6,570 hp and additional residual thrust of some 600 kg , were to give the High-Speed Bomber II a speed in excess of 870 km/h. The engines were mounted on two sponsons projecting at an angle of 45° above the fuselage; this arrangement being chosen to keep the exhaust gases and turbulent airflow from the propellers well away from the tail control surfaces. At the same time, the height of the engines above the ground meanl that the tricycle undercarriage required only the minimum of clearance.
The cantilevered low-wing design featured forward-swept wings - similar to the Junkers Ju 287 - with a negative sweep of 28.5°, combined with swept horizontal tail surface leading edges. Development work was carried out in the autumn of 1944, without a contract from the RLM, to test installation arrangements for turboprop engines.
Two BMW 109-028 turboprop engines, each with a shaft output of 6,570 hp and additional residual thrust of some 600 kg , were to give the High-Speed Bomber II a speed in excess of 870 km/h. The engines were mounted on two sponsons projecting at an angle of 45° above the fuselage; this arrangement being chosen to keep the exhaust gases and turbulent airflow from the propellers well away from the tail control surfaces. At the same time, the height of the engines above the ground meanl that the tricycle undercarriage required only the minimum of clearance.
The cantilevered low-wing design featured forward-swept wings - similar to the Junkers Ju 287 - with a negative sweep of 28.5°, combined with swept horizontal tail surface leading edges. Development work was carried out in the autumn of 1944, without a contract from the RLM, to test installation arrangements for turboprop engines.
