Type HD 63A Two seat trainer HD 63AwTwo seat trainer seaplane HD 63W Two seat trainer seaplane
Engine 1 Argus As 10C
Dimensions Length 8,20 m , height 2,70 m ,  span 10,80 m , wing area  24,4 m2 , Length 8,65 m , height 3,63 m ,  span 10,80 m , wing area  30,36 m2 ,
Weights Empty 820 kg, loaded 1250 kg , max. take off weight   Empty  kg, loaded  kg , max. take off weight   Empty 1000 kg, loaded 1400 kg , max. take off weight  
Performance Max.. speed 201 km/h at 1000 m, 188 km/h at sea level, 195 km/h at 2000 m, cruising speed  190 km/h, range 1100 km, endurance  , service ceiling  3500 m , climb to 1000 m 5 min. 12 sec., to 2000 m 12 min. 42 sec., to 3000 m 22 min. 24 sec. Max.. speed  km/h at 1000 m, km/h at sea level, km/h at 2000 m, cruising speed   km/h, range km, endurance  , service ceiling  3500 m , climb Max.. speed 177 km/h at 1000 m, climb to 1000 m 8 min., to 2000 m 19,7 min.  range 1100 km, service ceiling  3000 m, endurance 3 h
Armament Optional :1 front fixed 7.92 mm MG-17 machine gun
Type Werk.Nr Registration History
HD 63A 401 D-2219, D-IKIT
HD 63A 407 D-2329
HD 63A
HD 63A
HD 63Aw 402 D-2263 Sea plane, single seat, larger rudder
HD 63Aw Sea plane, single seat, larger rudder
HD 63Aw Increased span lower wing 10,8 m, wing area 30,36 m2
HD 63Aw Increased span lower wing 10,8 m, wing area 30,36 m2
HD 63Aw Increased span lower wing 10,8 m, wing area 30,36 m2
HD 63Aw Increased span lower wing 10,8 m, wing area 30,36 m2
The Heinkel He 63 was a trainer biplane built in Germany in the early 1930s. It was a largely conventional design with single-bay wings, fixed tailskid undercarriage, and two open cockpits in tandem. An unusual feature of the design was the highly swept, arrow-shaped upper wing, braced to the lower wing by N-type struts. Prototypes of the He 63 were built in both landplane and seaplane form, but no production ensued.
Wing structure:
Upper wing 12° swept, 1° V-shape, strongly staggered forward. Straight lower wing with 2° V-shape. Both wings in two parts, upper wing on canopy struts, lower wing attached to the fuselage sides. Between the wings N-shaped posts made of profile steel tubes. Bracing by profile wires. Pull cable from the front undercarriage connection to the upper front spar and from the lower front spar to the upper rear spar. Counter cable between the upper and lower rear spars. Two-spar wing with spars made of profile steel tubes, light metal ribs and fabric covering.
Fuselage :
Two open seats one behind the other. Steel tube framework with trapezoidal cross-section, made oval by light alloy form frames and stringers and covered with fabric. Front part of the fuselage up to the lower wing with light alloy sheet
Tail unit:
Free-standing vertical fin built in one piece with the fuselage, horizontal fin braced to the fuselage. Rudder without compensation with trim bar edge, elevator with aerodynamic and mass compensation. Ailerons only in the upper
wing. Ailerons controlled by pushrod from the underwing.
Engine:
Air-cooled eight-cylinder V-engine with overhead cylinders Argus As. 10 with 220 hp take-off power.Two-bladed wooden propeller with a diameter of 2.4 m with hub cover.Fuel tank in the fuselage.
Undercarriage:
Split axle, hinged to a V-strut in the middle, supported by a V-strut on the outside. Front leg of the V-strut sprung.Brakable wheels and sprung tail made of cast iron.
Armament:
A rigid MG 17 could be installed for training purposes.

Developed in collaboration with the DVS.Intended for observer, radio and photo training.The wheeled undercarriage could be replaced with floats