Top inlet flow field and inlet performance data are presented which provide preliminary insight into the feasibility of upper-fuselage mounted inlet systems for transonic-supersonic fighter aircraft. Presented data span the Mach 0.2 to 2.0 envelope and enable evaluation of the influence of key aircraft configuration variables - inlet location, wing position, wing leading-edge extension (LEX) planform area, and variable incidence canards - on top inlet performance. The viability of this concept relative to more conventional inlet/airframe integrations is assessed via comparative evaluation of top and conventional inlet flow field parameters at transonic and supersonic speeds. It is shown that the action of the wing LEX vortex system produces a significant improvement in top inlet performance. Currently available transonic-supersonic data indicate that top inlet systems pose a viable configuration option for fighter aircraft requiring moderate angle of attack capability. However, recently acquired data indicate that increased angle of attack capability may be obtained by increasing wing leading-edge sweep angle.


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    Title :

    Top inlet system feasibility for transonic-supersonic fighter aircraft applications


    Contributors:

    Conference:

    Aircraft Systems Meeting ; 1980 ; Anaheim, CA


    Publication date :

    1980-08-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :




    Top-mounted inlet system feasibility for transonic-supersonic fighter aircraft

    Williams, T. L. / Hunt, B. L. / Smeltzer, D. B. et al. | NTRS | 1981


    Top-Mounted Inlet System Feasibility for Transonic-Supersonic Fighter Aircraft

    T. L. Williams / B. L. Hunt / D. B. Smeltzer et al. | NTIS | 1981


    Top-mounted inlet system feasibility for transonic-subsonic fighter aircraft applications

    Williams, T. L. / Hunt, B. L. / Smeltzer, D. B. et al. | NTRS | 1981