Rolling and yawing moments due to both rolling velocity and acceleration were found to be highly dependent on frequency at angles of attack higher than 16°; oscillatory derivatives were much different at these high angles from same measured by steady state rolling flow tests.


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    Title :

    Experimental determination of effects of frequency and amplitude of oscillation on roll-stability derivatives for 60° delta-wing airplane model


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1960


    Size :

    49 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :