Inlet flow-field and compressor-face performance data were obtained for a 0.095-scale model of a VSTOL fighter-attack aircraft configuration with twin top-mounted inlets. Tests were conducted at Mach numbers from 0.6 to 2.0 and at angles of attack and sideslip up to 27 deg and 12 deg, respectively. The effects of inlet location, wing leading-edge extension planform area, canopy-dorsal integration, and variable incidence canards were determined. The results show that distortion at the compressor face when maneuvering is relatively low (20% or less) at Mach numbers up to 0.9. However, at Mach numbers of 1.2 and above, maneuverability may be restricted because of high distortion or low pressure recovery (80% or less) or both.


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    Titel :

    Airframe effects on top-mounted inlet systems for VSTOL fighter aircraft


    Beteiligte:
    Smeltzer, D. B. (Autor:in) / Nelms, W. P. (Autor:in) / Williams, T. L. (Autor:in)

    Kongress:

    V/STOL Conference ; 1981 ; Palo Alto, CA


    Erscheinungsdatum :

    1981-12-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Airframe effects on top-mounted inlet systems for VSTOL fighter aircraft

    SMELTZER, D. / NELMS, W. / WILLIAMS, T. | AIAA | 1981


    Airframe effects on a top-mounted fighter inlet system

    Smeltzer, D. B. / Nelms, W. P. / Williams, T. L. | NTRS | 1982


    Airframe effects on a top-mounted fighter inlet system

    SMELTZER, D. B. / NELMS, W. P. / WILLIAMS, T. L. | AIAA | 1982


    Study of aerodynamic technology for VSTOL fighter attack aircraft

    Burhans, W., Jr. / Crafta, V. J., Jr. / Dannenhoffer, N. et al. | NTRS | 1978


    Study of Aerodynamic Technology for VSTOL Fighter Attack Aircraft

    W. Burhans / V. J. Crafta / N. Dannenhoffer et al. | NTIS | 1978