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.


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    Titel :

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


    Beteiligte:

    Erscheinungsdatum :

    1973


    Format / Umfang :

    670 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch