Darmstadt D 9 "Konsul"
Type
Single seat glider
Dimensions
Length 6,35 m, span  18,2 m, wing area 21,0 m2, aspect ratio 15,8
Weights
Empty 185 kg, flying weight 270 kg, wing loading 9,1 kg/m2
Performance
Max. glide ratio 1:24,4 at 53 km/h
Type
Werk.Nr
Registration
History
     
Designed by  A. Botsch, R. Spies and F. Hoppe in 1923.  Profile inner wing Göttingen 535 and outer symmetric.
The D-9 Konsul first flew in 1923 and took part in both the 1923 and 1924 Rhön events. In 1923 the Konsul, flown by
Albert Botsch, one of its designers, won the distance prize with a record breaking flight of 18.7 km . In 1925 it won
the distance prize again, piloted by Johannes Nehring. Nehring set another distance record that year with a flight of
24.4 km  during a visit to the Crimea, hill soaring as before. The Konsul remained active until 1927 when it was
destroyed in an accident.
Development
The Akademische Fliergruppe of the Technical University of Darmstadt was first formed in 1921. It was, and is, a group of aeronautical students who design and construct aircraft as part of their studies and with the help and encouragement of their University. The 1923 D-9 monoplane was named in honour of Karl Kotzenberg, sometime Consul General to Norway, who had provided financial support for the project. It was the most advanced glider of its day and had the highest aspect ratio (initially 16.66) of any existing aircraft.
The Konsul was a wood framed aircraft with a high, cantilever, single spar wing with stressed 3-ply covering from the spar to the leading edge and fabric covered aft. It was built in three parts, an 8 m (26 ft 3 in) inner section with a box spar and outer panels with an I-section one. The wing had a thick and strongly cambered profile, using the then new Göttingen 535 airfoil with its high lift to drag ratio that attracted many pre-World War II sailplane designers. The long wings had constant chord except for tapered tips, where the wing decreased in thickness. There was no dihedral. Half span, large area ailerons had angled hinges attached to the spar at its tip and, in the early flight tests, projected well beyond the fixed wing tip. These proved both heavy in flight and vulnerable on the ground, so were soon tapered and rounded off, slightly reducing the span and aspect ratio. The ailerons operated differentially, upward deflections being smaller than downward ones; this was a relatively new way of reducing adverse yaw but in addition the rudder and ailerons were interconnected. Small rudder deflections did not affect the ailerons but larger ones moved them appropriately. No flaps, airbrakes or spoilers were fitted, normal for the time
The fuselage of the Konsul was a 3-ply skinned, oval cross sectioned semi-monocoque, with a blunt nose and slightly tapered and more rounded towards the tail. The open, unscreened cockpit was well ahead of the wing, which was mounted directly on top of the fuselage. A short undercarriage skid was attached to the fuselage underside via rubber blocks, aided by a small tailskid. The empennage was fabric covered, straight edged with angled tips; the fin and tailplane had narrower chord than the generous control surfaces and slight sweep on their leading edges. The rudder, which reached down to the bottom of the fuselage, moved within a cut-out in the elevators.