The Ho VIII, Transport Aircraft and Flying Wind Tunnel




Fuselage Construction

Steel Tube


Wing Construction






Three people


Motor type


Six Argus As 10 engines




6 x 176 kW (6 x 236 HP)



40.0 m


Sweep Angle


33.7 degrees


Taper Ratio




Wing Root Thickness


18% chord


Wing Root Depth


6.5 m


Rib Spacing


0.4 m


Wing Area


146.0 m2


Aspect Ratio




Pilot position




Mid-section width


4.0 m


Cockpit width


0.80 m


Cockpit height (from seat)


1.1 m


Empty weight


5000 kg


Ballast (water)




Additional payload


240 kg




2760 kg


Maximum weight


82000 kg


Wing loading


55 kg/m2


Engine loading

(5.55) 7.6 kg/kW


Stall speed


80 km/h


Landing speed


80 km/h


Cruise speed


250 km/h


Maximum speed (horizontal)

280 km/h


Maximum speed


430 km/h

I was invited to attend a high level meeting with Goering, where the prospect of a long range bomber was discussed. The official demand was: 4000 kg bombs, and 4000 mile range. The Junkers 287 was to be compared with other proposals. Messerschmitt submitted one, we another. Six Jumo 004 jet engines were suggested as powerplants for all.

 After three days of discussions, it became clear that our flying wing would have far better range than the others, although short of the required 4000 miles. Thus it appeared that an order for a large bomber would come our way, so we decided to build an intermediate size aircraft to gain experience.

To minimize the risk of aerodynamic surprises, we simply doubled the dimensions of the trusty Ho III. This improved the calculated L/D to 30, since the friction drag coefficient was reduced through a fivefold increase in the Re numbers.

 All our calculations needed verification in a wind tunnel. As they remained unavailable, we decided to help ourselves, and put a tube shaped fuselage in the Ho VIII, to make it a flying wind tunnel.

 The Argus engine used in the Ho VII would be used, with six units mounted in the wings driving pusher propellers. The wing would have a box spar, with all control rods and cables inside the spar, to free the remaining wing space for fuel tanks.

 The construction progressed quickly through the spring of 1945, and the aircraft was half finished when the American forces reached Gottingen.


Control linkage for the Ho VIII