The Ho Parabel (Parabola)

Usage
 

Experimental

Fuselage Construction

Steel tube
 

Wing Construction
 

Wood
 

Capacity
 

One person
 

Span
 

12 m
 

Sweep Angle
 

---
 

Taper Ratio
 

9.5
 

Wing Root Thickness
 

16% chord
 

Wing Root Depth
 

3.8 m
 

Rib Spacing
 

0.4 m (0.20 at the leading edge)

Wing Area
 

33 m2
 

Aspect Ratio
 

4.4
 

Pilot position
 

Seated
 

Mid-section width
 

2.4 m
 

Cockpit width
 

0.80 m
 

Cockpit height (from seat)
 

0.90 m
 

Empty weight
 

90 kg
 

Ballast (water)
 

---
 

Additional payload
 

80 kg
 

Maximum weight
 

170 kg
 

Wing loading
 

5.15 kg/m2
 

Stall speed
 

30 km/h
 

Landing speed
 

30 km/h
 

Minimum Sink
 

0.80 m/s at 45 km/h and 5.15 kg/m2 loading

Best Glide Ratio
 

19.5:1 at 61.5 km/h and 5.15 kg/m2 loading

Maximum Speed
 

164 km/h
 
The progress toward the solution of the "middle-effect" problem that was made with the stepped sweepback of the Ho V led us to believe that the continuous curve of the parabola would be the final solution. But we needed proof! So, along with the first Ho III, the Parabola was built in 1938.

 It was a very light sailplane, with only a 12 meter span, and suitable only for altitude flights, as it lacked the ability to penetrate into the wind. Since it was vulnerable in gusts, large elevon surfaces were used to maintain control. These functioned as rudder, as well as aileron/elevator.

The aircraft warped severely during winter storage, and was scrapped without ever being flown.