The feasibility of operating tilting-prop-rotor aircraft at high speeds is examined by calculating the performance, stability, and maneuverability of representative configurations. The rotor performance is examined in high-speed cruise and in hover. The whirl-flutter stability of the coupled-wing and rotor motion is calculated in the cruise mode. Maneuverability is examined in terms of the rotor-thrust limit during turns in helicopter configuration. Rotor airfoils, rotor-hub configuration, wing airfoil, and airframe structural weights representing demonstrated advance technology are discussed. Key rotor and airframe parameters are optimized for high-speed performance and stability. The basic aircraft-design parameters are optimized for minimum gross weight. To provide a focus for the calculations, two high-speed tilt-rotor aircraft are considered: a 46-passenger, civil transport and an air-combat/escort fighter, both with design speeds of about 400 knots. It is concluded that such high-speed tilt-rotor aircraft are quite practical.


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    Title :

    Calculated Performance, Stability and Maneuverability of High-Speed Tilting-Prop-Rotor Aircraft


    Contributors:
    W. Johnson (author) / B. H. Lau (author) / J. V. Bowles (author)

    Publication date :

    1986


    Size :

    45 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Calculated performance, stability, and maneuverability of high-speed tilting-prop-rotor aircraft

    Johnson, Wayne / Lau, Benton H. / Bowles, Jeffrey V. | NTRS | 1986


    Calculated performance, stability and maneuverability of high-speed tilting-prop-rotor aircraft

    Johnson, Wayne / Lau, Benton H. / Bowles, Jeffrey V. | NTRS | 1986



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