It is assumed that the variation in the lift-to-drag ratio with lift of the caret wing is typical of that of a lifting configuration for Mach numbers in the range where nozzle deflections are most significant. Numerical optimization studies using this assumption show that optimum nozzle thrust deflection angles are commonly 50% larger than those suggested by analyses at constant lift-to-drag ratio. Analytical results are obtained for the optimum deflection angle based on Newtonian, Busemann second order and linear theory relationships. (Author)


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    Title :

    Optimum Engine Thrust Deflection for High-Speed Cruising Aircraft


    Contributors:
    J. Pike (author)

    Publication date :

    1972


    Size :

    43 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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