Aerodynamic force and moment equations are developed for 6-DOF missile simulations of both the ascent phase of flight and a tumbling re-entry. The missile coordinate frame (M frame) and a frame parallel to the M frame were used for formulating the aerodynamic equations. The missile configuration chosen as an example is a cylinder with fixed fins and a nose cone. The equations include both the static aerodynamic coefficients and the aerodynamic damping derivatives. The inclusion of aerodynamic damping is essential for simulating a tumbling re-entry. Appended information provides insight into aerodynamic damping.


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    Title :

    Missile Aerodynamics for Ascent and Re-entry


    Contributors:

    Publication date :

    2012-11-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :


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