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Aachen FVA-17 "Nurflügler"

In 1954, the FVA took a research commissioned by the Federal Ministry of Transport for the purpose of operating the type certification of the Horten Ho-33 V1 flying wing powered aircraft.
The aircraft was already designed with a view to later use it as powered aircraft.
Since the VI had first flown as a glider, the proposed engine weight was installed as ballast.
Design approval for the tailless Ho33-V1 powered aircraft was achieved in 1955.
The first two test samples of Ho 33 were built by Alfons Pützer KG in Bonn. The first calculation of the data used were the following:
Wingspan: 19.20 m
Chord at the root: 3.25m
Wing area: 35,60sq.m
Net weight: 430kg
Flying weight: approx 650kg
Wing loading: 18kg / sq.m
The hull was like the wings, made ​​of wood construction with two seats in tandem. In the rear fuselage space for the engine was provided.
Tandem undercarriage with a steerable tail wheel and two retractable support wheels, about in the inner third of the half span were fitted.
The fuselage was transferred by Pützer to Aachen in the FVA workshop, where work was started for the engine installation. The powerplant was a Zündapp "Z 9-092".
Power: 50 hp at 2300 rev / min
Consumption: 210285 g / hp-hr
Weight: approx 65 kg
This work took about four months to complete. The fuselage was returned to Bonn and transferred to Aachen after some trial launchs at Bonn again. While at the same weight ​​for the purpose of determining the center of gravity, it turned out that the weights were far exceeded. With an empty weight of 620 kg the flying weight was about 850 kg.
It was prepared the launch in Merzbrück some difficulties. The Horten was transported for further testing in flight 33 at Noervenich. The entire aircraft was re-measured in almost all parts. The sparse drawings not agree with the construction.
The test flights at Noervenich proved, among other things, that behavior and the start was not satisfactory.
The regulations and guidelines of CAR Part 3 were applied and the new flight weight of about 900 kg; the geometrical data remained unchanged. As might be expected, the air loads were significantly higher than the original. The loads were set up as part of a student research project at the Department of Aviation.
The strength analysis was performed on the basis of newly data obtained during the survey of the aircraft ​​ resulting in air loads for the main components. The aircraft was undersized for the stresses occurring in some parts.
In particular, the suspension was of insufficient dimensions. More flights did not appear advisable because of the lack of strength. The changes required meant such an effort would exceed the financial resources so the job could not be continued. The aircraft was returned to Bonn leading to the abandonment of the project.


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