Data was obtained by tracking rocket-propelled bodies carrying wings of various plan forms. Results showed that for investigations in Mach number range of 1.05 - 1.35, an increasing swept-back angle and decreasing aspect ratio reduced the value of wing drag coefficient. Decreasing the aspect ratio always decreased the wing drag coefficient; although, this effect was observed to become very small at higher swept-back angles.


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    Title :

    Drag Characteristics of Rectangular and Swept-Back NACA 65-009 Airfoils Having Aspect Ratios of 1.5 and 2.7 as determined by Flight Tests at Supersonic Speeds


    Contributors:
    S. R. Alexander (author) / E. Katz (author)

    Publication date :

    1947


    Size :

    23 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English