A.A. Cal, J.R. Banerjee

The Cranfield aerobatic aircraft A1 is analysed for flutter, stability and dynamic response using the basic data of the aircraft together with some available ground resonance test results. The method used is based on normal mode approach, linking strip theory and modified unsteady aerodynamics of Theodorsen type. First, a dynamic stability analysis is carried out using conventional stability derivative method, but with flexibility and unsteady aerodynamics partially incorporated. Then an unsteady downwash effect is introduced and the subsequent results are compared with the flight test data. Symmetric and antisymmetric flutter speeds are calculated with and without the inclusion of rigid-body freedoms of the aircraft. In the final part of the investigation, the response of the Cranfield A1 to both discrete gusts and continuous atmospheric turbulence is independently studied. The results obtained from the two gust models show a correlation (overlap) between the two, which accords with earlier investigations carried out by the Royal Aerospace Establishment, U.K and the American aerospace agency NASA. Results obtained are discussed in detail and commented on.

International Forum on Aeroelasticity and Structural Dynamics 1991, Aachen

Conference Paper

englisch

21,0 x 29,7 cm, 16 Seiten

DGLR-Bericht, 1991, 1991-06, International Forum on Aeroelasticity and Structural Dynamics 1991 Proceedings; S.562-577; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroelasticity

Bestellbar

1991