Ho Vb Built with Conventional Methods




Fuselage Construction

Steel tube


Wing Construction






Two People Abreast


Motor type


Two Hirth HM 60R engine




2 x 59 kW (2 x 79 HP)




16.0 m


Sweep Angle


25.5 degrees (outer wings 36 degrees)

Taper Ratio




Wing Root Thickness


16% chord


Wing Root Depth


4.5 m


Rib Spacing


0.4 m (0.2 meters at the leading edge)

Wing Area


38.0 m2


Aspect Ratio




Pilot position




Mid-section width


4.0 m


Cockpit width


0.80 m


Cockpit height (from seat)


1.0 m


Empty weight


1360 kg


Ballast (water)




Additional payload


160 kg




80 kg


Maximum weight


1600 kg


Wing loading


38.0 kg/m2


Engine loading

13.5 kg/kW


Stall speed


82 km/h


Landing speed


70 km/h


Cruise speed


230 km/h


Maximum speed (horizontal)

260 km/h


Maximum speed


350 km/h

The second Ho V was started in Cologne in 1937. Our new knowledge about the "middle-effect" allowed us to build a canopy over the cockpit, and put the pilots in a more upright position. It was believed that the uncomfortable reclining position was a contributing factor in the Ho V a crash. We also returned to the normal elevon configuration, and increased the wing span by six feet. The airfoil and the stepped leading edge sweepback were retained. The landing gear was a fixed tricycle type. A split flap on the center section was connected to trailing edge flaps along the inboard half of each wing.

 The flight characteristics were excellent in all respects. During landing, a surprising discovery was made; air trapped in ground effect between the deep center section and the flaps rotated the aircraft slightly and lowered it gently to the ground. The pilot needed only to pull the stick all the way back and wait. It was impossible to make a hard landing!