Transonic wind tunnel tests were performed in an Calspan Corporation (formerly Cornell Aeronautical Laboratory) Eight-Foot Transonic Wind Tunnel on a missile model with canard wings. The tests were conducted during the end of April and the beginning of May, 1973. Two distinctly different investigations were made. The effect of canard wing positions, canard - tail angular orientation, canard size, model roll angle, and nose shape, were investigated during the Aerodynamic Test Phase. The use of canard wings for roll attitude control was also investigated during this phase. The effect of different jet plumes on the aerodynamic model loads were studied during the Thrust Effect Phase. A normal jet plume simulator was used and the effects of model tail position, planform, and orientation were investigated. The report presents details of the test program and the results in tabular form.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Transonic Wind Tunnel Tests on a Missile Model with Canard Wings. Volume I


    Contributors:

    Publication date :

    1973


    Size :

    670 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English