I. Ae. 34 (Ho XV)

I. Ae. 34a

Three two place sailplanes were laid out in 1948, and completed the following year. With these aircraft, I hoped to fill six basic requirements with minimum expense, while standardizing the equipment:

1. Provide a two-place training glider, that could fly for extended periods in thermals, in order to keep training costs down.
2. Provide good visibility for the instructor while the student was practicing "blind flying" on instruments.
3. Provide a suitable glider for the student's first solo flight.
4. Provide an adequately stressed airframe for acrobatic maneuvers.
5. Provide a structure that could easily be converted to a motorglider.
6. Provide a high performance competition sailplane.
7. The "in house" designation for the I. Ae. 34 became the Ho XV a. The official description was as follows:

The single spar all wood structure consists of three parts, with a 60 cm wide center section. The entire wing is plywood covered, with elevons and flaps along the trailing edge. The elevons are balanced with lead weights. Ball bearings support all pushrods. Drag-rudders retract flush into the wing tips, and terminal velocity airbrakes are installed near the wing roots. The wing can be removed by four people in a few minutes. The all wood center section has two tandem wheels near the center of gravity, with a skid in front, to enable it to make off field landings without danger of flipping over. The rear seat is located 30 cm above the front, giving both pilots identical view. A single instrument panel is visible from both cockpits. Provisions for oxygen and seat parachutes are included. The rear control stick may be removed for passenger flying.

I. Ae. 34b (Ho XVb)

Two Ho 15b aircraft were built for the World Soaring Championship in Spain in 1952. Time did not permit much testing or training before the aircraft had to be shipped abroad.

Reimar Horten says in his biography:

This single seater (m = mono plaza) was almost identical to the two place model, except that two retractable motorscooter wheels replaced the original landing gear, and the flaps were eliminated.

Two aircraft were built for the World Soaring Championship in Spain in 1952. Time did not permit much testing or training before the aircraft had to be shipped abroad.

Our fortune in Spain was not good. One of the sailplanes was destroyed in a landing during the practice days. The other was seriously damaged on the fourth contest day, and unable to continue.

Specifications - I. Ae. 34a

Usage	Performance Sailplane
Fuselage Construction	Wood
Wing Construction	Wood
Capacity	Two people
Span	18 m
Sweep Angle	21.8 degrees
Taper Ratio	5
Wing Root Thickness	18% chord
Wing Root Depth	1.75 m
Rib Spacing	0.4 m
Wing Area	18.9 m2
Aspect Ratio	17.1
Pilot position	Seated
Mid-section width	0.8 m
Cockpit width	0.80 m
Cockpit height (from seat)	---
Empty weight	270 kg
Ballast	water)
Additional payload	180 kg
Maximum weight	430 kg
Wing loading	22.7 kg/m2
Stall speed	65 km/h
Landing speed	65 km/h
Minimum Sink	0.75 m/s at 70 km/h and 22.7 kg/m2 loading
Best Glide Ratio	28:1 at 88 km/h and 22.7 kg/m2 loading
Maximum Speed	250 km/h