Ho Vb Built with Conventional Methods

Usage
 

Experimental

Fuselage Construction

Steel tube
 

Wing Construction
 

Wood
 

Capacity
 

Two People Abreast
 

Motor type
 

Two Hirth HM 60R engine
 

Power
 

2 x 59 kW (2 x 79 HP)
 

Span
 

16.0 m
 

Sweep Angle
 

25.5 degrees (outer wings 36 degrees)

Taper Ratio
 

6.4
 

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
 

6.75
 

Pilot position
 

Seated
 

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
 

Fuel
 

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!