Procedures for the numerical modeling of airplane spin phenomena with related aerodynamic considerations are presented. All six degrees of freedom are conserved during the motion and modeling of flow is performed by a computational procedure for 2D wakes. Spinning tests on light airplanes show that the pressure for a given domain and moment is constant. Wake pressure is a function of the general structure of the airplane and is submitted to the reaction of the single airplane components.
Beitrag Zur Numerischen Simulation der Trudelbewegung von Flugzeugen (Contribution to the Numerical Solution of Airplane Spin Motion)
1987
159 pages
Report
No indication
English
Beitrag zur numerischen Simulation der Trudelbewegung von Flugzeugen
Tema Archive | 1987
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