Abstract
For the purpose of simulating a flight of a flapping vehicle a test device with a circular flight has been developed. The device provides us a flight speed, the trimmed pitch angle and the generated lift force which can be derived from the angle of a vertical arm. Thanks to this device, the appropriate parameters to achieve a stable flight can be set in advance without damaging a vehicle, such as the flapping frequency, the feathering angle and the elevator angle. In the present paper the deriviation of the lift and pitching moment generated by a flapping motion is described.
