Investigation was conducted in Langley 4- by 4-ft supersonic pressure tunnel; 5 models were tested with fineness ratios varying from 19.1 to 14.8; tests covered angle-of-attack range up to about 28° for complete configuration and various combinations of component parts.


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    Title :

    Aerodynamic characteristics in pitch of series of cruciform-wing missiles with canard controls at mach number of 2.01


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1961


    Size :

    40 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English