| Type | Single seat glider (Pilot laying down) | |
| Dimensions | Length 5,1 m, height 1,82 m, span 10,0 m, wing area 12 m2, aspect ratio 8,33, mean chord 1,2 m, chord at wing root 1,3 m, dihedral 5º, width 0,58 m, frontal area 0,35 m2, stabilizer 1,8 m2, elevator 1,8 m2, fin 0,9 m2, rudder 0,9 m2 | |
| Weights | Empty 90 kg, flying weight 170 kg, wing load 14,17 kg/m2 | |
| Performance | Max. speed 450 km/h, glide ratio 19,8 at 81 km/h, min. descent 0,68 m/sec. at 64 km/h, max. load factor 14 g | |
| Type | Werk.Nr | Registration | History | |
| Built in 1937, first flight 21/3 1938 | ||||
The fs 17 was designed to find out whether a lying pilot can fly with feeling and enough endurance. The arrangement with a lying pilot allows a smaller cross sectional area an thus less drag. In addition a lying pilot can better bear higher load factors. In the literature the members of the Akaflieg coun't find anything and the opinions of the experts differed. Practical test haven't been done since the days of the Wright brothers.
The pilot's safety was emphasized in this project because the pilot appeared to be more endangered due to his arrangement. The aircraft was therefore designed as a low wing plane with an extra stiff fuselage. Stall safety and a good efficiency of the ailerons in low speed flight were also important design features.
Since the fs 17 was pure experiment aircraft, some other test were included, too, because the constructors didn't want to test them on high performance planes. For example it was tested whether the wing spar should also absorb torsion, because the then usual torsion noses deteriorated after some time. New airbrakes were tested, installed in the tail of the fuselage
The pilot's safety was emphasized in this project because the pilot appeared to be more endangered due to his arrangement. The aircraft was therefore designed as a low wing plane with an extra stiff fuselage. Stall safety and a good efficiency of the ailerons in low speed flight were also important design features.
Since the fs 17 was pure experiment aircraft, some other test were included, too, because the constructors didn't want to test them on high performance planes. For example it was tested whether the wing spar should also absorb torsion, because the then usual torsion noses deteriorated after some time. New airbrakes were tested, installed in the tail of the fuselage
