An experimental investigation of a full scale mixed compression inlet sized for the TF30-P-3 turbofan engine was conducted at Mach 2.5 and 2.0 operating conditions. The two cone axisymmetric inlet had minimum internal contraction consistent with high total pressure recovery and low cowl drag. At Mach 2.5, inlet recovery exceeded 0.90 with only 0.02 centerbody bleed mass-flow ratio and zero cowl bleed. A centerbody bleed of approximately 0.05 gave a maximum inlet unstart angle-of-attack of 6.85 deg. Inlet performance and angle-of-attack tolerance is presented for operation at Mach 2.5 and 2.0.


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    Title :

    Minimizing boundary layer bleed for a mixed compression inlet


    Contributors:

    Conference:

    Propulsion Joint Specialist Conf. ; 1973 ; Las Vegas, NV, United States


    Publication date :

    1973-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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