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.


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    Title :

    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


    Contributors:

    Publication date :

    1980


    Size :

    56 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Instationäre Beiwerte von Flugkörpern : Derivative der Längsstabilität von Flügel-Rumpf-Anordnungen mit hohen Anstellwinkeln in Unterschallströmung

    Deutschland, Bundesminister der Verteidigung, Bundesrepublik / Deutschland, Dokumentationszentrum der Bundeswehr, Bundesrepublik | TIBKAT | 1978



    Simple Wings Unsteady Aerodynamics at High Angles of Attack: Experimental and Modeling Results

    Abramov, N. / Goman, M. / Khrabrov, A. et al. | British Library Conference Proceedings | 1999