A theoretical method for the determination of unsteady aerodynamic coefficients associated with the longitudinal stability of slender wings in supersonic flight is presented. It is based on the indicial functional theory of Tobak. Extension to higher incidences is effected by combining the indicial functions with steady nonlinear coefficients derived from a semiempiricial procedure. The unsteady nonlinear aerodynamic coefficients are determined for delta wings with subsonic and supersonic leading edges, respectively.
Unsteady Aerodynamics of Missiles. Part 3: Determination of the Longitudinal Stability of Wings at High Angles of Attack in Supersonic Flight Instationaere Beiwerte von Flugkoerpern, Teil 3. Derivative der Laengsstabilitaet von Fluegeln bei Hohen Anstellwinkeln in Ueberschallstroemung
1980
56 pages
Report
No indication
English
Simple Wings Unsteady Aerodynamics at High Angles of Attack: Experimental and Modeling Results
British Library Conference Proceedings | 1999
|