The low-speed characteristics of a large-scale model of the U. S. Navy/Grumman F-14A aircraft were studied in tests conducted in the Ames Research Center 40- by 80-Foot Wind Tunnel. The primary purpose of the program was the determination of lift and stability levels and landing approach attitude of the aircraft in its high-lift configuration. Tests were conducted at wing angles of attack between minus 2 deg and 30 deg with zero yaw. Data were taken at Reynolds numbers ranging from 3.48 million to 9.64 million based on a wing mean aerodynamic chord of 7.36 ft. The model configuration was changed as required to show the effects of glove slat, wing slat leading-edge radius, cold flow ducting, flap deflection, direct lift control (spoilers), horizontal tail, speed brake, landing gear and missiles. (Author)


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    Title :

    Low-Speed Wind-Tunnel Investigation of the Longitudinal Characteristics of a Large-Scale Variable Wing-Sweep Fighter Model in the High-Lift Configuration


    Contributors:
    W. T. Eckert (author) / R. L. Maki (author)

    Publication date :

    1973


    Size :

    85 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English