By applying momentum theory to lifting wings and propulsion systems with deflected thrust, it is shown that when these components are combined in single lifting system, minimum ideal thrust or power is required in any flight condition when momentum deflection angles of wing wake and propulsive jet or slipstream are approximately equal; V /STOL aircraft systems having closely coupled wing and propulsive flows more or less automatically satisfy this rule, and therefore, approach minimum ideal thrust or power requirements; comparisons of theory with flight and wind tunnel measurements seem to bear out this prediction even when lift due to power does not extend across whole wing span.


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    Title :

    Momentum rule for optimum aircraft performance in V/STOL transition regime


    Additional title:

    Canada. Nat Research Council -- Aeronautical Report


    Contributors:


    Publication date :

    1967


    Size :

    43 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :