A wind-tunnel investigation was conducted to examine the low-speed static stability and control characteristics of a 0.10 scale model of a STOL supersonic cruise fighter concept. The concept, referred to as a twin boom fighter, was designed as a STOL aircraft capable of efficient long range supersonic cruise. The configuration name is derived from the long twin booms extending aft of the engine to the twin vertical tails which support a high center horizontal tail. The propulsion system features a two dimensional thrust vectoring exhaust nozzle which is located so that the nozzle hinge line is near the aircraft center of gravity. This arrangement is intended to allow large thrust vector angles to be used to obtain significant values of powered lift, while minimizing pitching moment trim changes. Low speed stability and control information was obtained over an angle of attack range including the stall. A study of jet induced power effects was included.


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    Title :

    Low-Speed Wind-Tunnel Test of a STOL Supersonic-Cruise Fighter Concept


    Contributors:
    P. L. Coe (author) / D. R. Riley (author)

    Publication date :

    1988


    Size :

    43 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Low-speed wind-tunnel test of a STOL supersonic-cruise fighter concept

    Coe, Paul L., Jr. / Riley, Donald R. | NTRS | 1988


    Development and Analysis of a STOL Supersonic Cruise Fighter Concept

    S. M. Dollyhigh / W. E. Foss / S. J. Morris et al. | NTIS | 1984


    Development and analysis of a STOL supersonic cruise fighter concept

    Dollyhigh, S. M. / Foss, W. E., Jr. / Morris, S. J., Jr. et al. | NTRS | 1984