A computational procedure has been developed for predicting the time dependent longitudinal and lateral aerodynamic characteristics of wing-body configurations at angles of attack up to and beyond stall. The purpose of the procedure is to provide the aircraft designer with a tool for simulating and alleviating such adverse wing stalling characteristics as wing rock, wing drop, loss of roll control or roll control reversal, etc. and thereby lead to the design of aircraft with improved stall, departure and spin resistance characteristics. The procedure is based on nonlinear lifting line theory which has been modified to include unsteady wake effects.


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    Title :

    Nonlinear Lifting Line Theory for Predicting Stalling Instabilities on Wings of Moderate Aspect Ratio


    Contributors:

    Publication date :

    1976


    Size :

    97 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English







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