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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    Titel :

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


    Beteiligte:
    W. T. Eckert (Autor:in) / R. L. Maki (Autor:in)

    Erscheinungsdatum :

    1973


    Format / Umfang :

    85 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch