Type Single seat
Engine 1 Douglas motorcycle engine  346 cm3 driving through a 1 m shaft a 2-bladed wooden propeller Ø 1.25 m. Fuel 27 l, fuel consumption 3.5 l/h
Dimensions Length 5,27 m , height  ,  span 10,0 m , wing area  10,0 m2, aspect rati 10,0 ,
Weights Empty 125 kg, loaded 235 kg , max. take off weight  
Performance Max.. speed  115 km/h, cruising speed 125 km/h  , service ceiling 3000 m  , climb to 1000 m 24 min,  landing speed 55 km/h
Type Werk.Nr Registration History
Rote Vogel I Completed in the second week of August 1924. A first start attempt on the evening of 14.8.
had to be aborted prematurely because the machine was not properly balanced. After using the elevator with
5 kg of lead, the first flight could take place on August 15th. Bäumer held the machine during the take-off
intentionally long on the ground and only took off after 200 m. The B I climbed faster than expected and showed good all-round flight characteristics. It proved very stable and could be flown with the stick released, although that tail unit had no damping surfaces (fins). The first test flight lasted 15 minutes, the altitude reached was 150 m. On landing, the undercarriage, which was too lightly built, broke, fortunately without the pilot or airframe being damaged.
On December 29, 1924,  broke during the start of a record flight
Rote Vogel II Was completed in April/May 1926 and immediately loaded by train to Düsseldorf. there from May to October 1926 took part in  the GESOLEI (Exhibition for Health Care, Social Welfare and Physical Education).After returning from the GESOLEI, major repairs to the cell of the "Red Bird" were required, which lasted until in
December. The first test flight took place in Fuhlsbüttel on December 15, 1926, with Paul Bäumer at the controls. In the second half of 1927, the flight station of the research institute of the Rhön-Rossitten-Gesellschaft (later DFS, German research institute for gliding)  used it successfully for scientific research ascents. In 1928 the Bäumer motor glider unfortunately had to be put out of operation because parts of the airframe were age-related material fatigue no longer corresponded to the strength specifications. A general overhaul was nt worthwhile
Single-seat, self-launching motor glider. Wooden cell with plywood planking.
Cantilever three-piece wing in shoulder-wing configuration; Center piece rectangular, outer wings trapezoidal. Two-beam construction, mostly lattice beams with double pressure belts; grid ribs. parallel spars in the center wing, tapering towards each other in the outer wings.
Hull with high oval cross-section. Fuselage framework consisting of 13 elliptical plywood frames, connected to one another by milled longitudinal spars. Pilot's seat deep in the fuselage below the wing leading edge; rectangular torso cutout fabric covered.
Rectangular tail. Balanced balance rudders without damping fins; Elevator undivided.
Chassis consisting of two rubber wheels on the side of the fuselage, continuous axle and suspension in the fuselage interior. Leather rollball under the tip of the fuselage, auxiliary skid in the tail.
The engine is a Douglas motorcycle engine 346 cm3, power 8/10 hp. Installation in the fuselage behind the driver's seat in the Center of gravity of the aircraft, supported directly on the chassis axis. Power transmission via chain to a larger one Gear wheel (reduction 34:16), housed in the supporting deck and firmly connected to a remote shaft of about 1 m in length was. The shaft drove the two-bladed wooden propeller (diameter 1.25 m) above the fuselage tip and was mounted on a trestle made of teardrop-shaped profiled wooden slats. Fuel tank with a capacity of 27 liters installed in the wing-fuselage transition. Gasoline consumption 3.5 liters per hour.