Recent developments in supersonic flow theory are applied to obtain estimates of the lift-drag ratios that may be achieved by aircraft employing sweptback wings. Lift-drag ratios greater than 10 to 1 can be maintained up to a Mach number of 1.4by the use of large angles of sweep and high aspect ratios. As the speed increases in the supersonic range the attainable lift-drag ratios decrease and the gain due to sweepback also appears to diminish. An efficient configuration for M = 1.4 would require about 60 deg sweepback, an aspect ratio of 4 and a wing loading of one third the atmospheric pressure. For a wing loading of 50 pounds per square foot the cruising altitude would be 60,000 feet and the indicated airspeed 290 miles per hour.


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    Title :

    Estimated Lift-Drag Ratios at Supersonic Speed


    Contributors:


    Publication date :

    1976-02-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :


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