The Ho III f Prone Position Glider

Usage
 

Trainer Sailplane for Prone Position Aircraft

Fuselage Construction

Steel tube
 

Wing Construction
 

Wood
 

Capacity
 

Pilot
 

Span
 

20.5 m
 

Sweep Angle
 

24.3 degrees
 

Taper Ratio
 

8.0
 

Wing Root Thickness
 

20% chord
 

Wing Root Depth
 

3.25 m
 

Rib Spacing
 

0.2 m
 

Wing Area
 

37.5 m2
 

Aspect Ratio
 

11.1
 

Pilot position
 

Seated

Mid-section width
 

2.4 m
 

Cockpit width
 

0.8 m
 

Cockpit height (from seat)
 

0.95 m
 

Empty weight
 

280 kg
 

Ballast (water)
 

---
 

Additional payload
 

80 kg
 

Maximum weight
 

360 kg
 

Wing loading
 

9.6 kg/m2
 

Stall speed
 

41 km/h
 

Landing speed
 

41 km/h
 

Minimum Sink
 

0.52 m/s at 47 km/h and 9.6 kg/m2 loading

Best Glide Ratio
 

28:1 at 63 km/h and 9.6 kg/m2 loading

Maximum speed
 

210 km/h
 
Three Ho III b's were modified in 1943 to familiarize pilots with the prone position used in the Ho IV and planned for our supersonic aircraft.

This position had several advantages: it was less tiring on long flights, one could endure higher g-loads, the visibility to the front and down was unsurpassed, and a smaller cockpit cross section could be used. Crash survival was also found to be very good.

 Ho III F, LA-AF, accumulated 100 flying hours in less than a year at the Klippeneck airfield. It was the first flying wing to be tested with a c/g launch hook.