Flow phenomena of the F-111A air intake system were investigated over a large range of Mach number, altitude, and angle of attack. Boundary-layer variations are shown for the fuselage splitter plate and inlet entrance stations. Inlet performance is shown in terms of pressure recovery, airflow, mass-flow ratio, turbulence factor, distortion factor, and power spectral density. The fuselage boundary layer was found to be not completely removed from the upper portion of the splitter plate at all Mach numbers investigated. Inlet boundary-layer ingestion started at approximately Mach 1.6 near the translating spike and cone. Pressure-recovery distribution at the compressor face showed increasing distortion with increasing angle of attack and system on an F-111A airplane increasing Mach number. The time-averaged distortion-factor value approached 1300, which is near the distortion tolerance of the engine at Mach numbers above 2.1. (Author)


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    Title :

    Flight-Determined Characteristics of an Air Intake System on an F-111A Airplane


    Contributors:

    Publication date :

    1972


    Size :

    66 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    Flight-determined characteristics of an air intake system on an F-111A airplane

    Hughes, Donald L. / Holzman, Jon K. / Johnson, Harold J. | TIBKAT | 1972


    Flight-determined stability and control coefficients of the F-111A airplane

    Iliff, K. W. / Maine, R. E. / Steers, S. T. | NTRS | 1978


    Flight-Determined Stability and Control Coefficients of the F-111A Airplane

    K. W. Iliff / R. E. Maine / S. T. Steers | NTIS | 1978