The Ho Parabel (Parabola)




Fuselage Construction

Steel tube


Wing Construction






One person




12 m


Sweep Angle




Taper Ratio




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




Pilot position




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.