Improved calculation of high speed inlet flows. Part II: Results

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An improved numerical algorithm that solves the full mean compressible Navier-Stokes equations has been applied to the calculation of the flowfield in three separate configurations of a simulated high speed aircraft inlet. The inlet geometry consists of a converging supersonic diffuser, formed by two nonparallel plates, followed by a constant height "throat." For all cases, the freestream Mach number is 3.51, and the Reynolds number is 13.6 × 106 based on the inlet length. The three configurations are characterized by different values of the angle of the converging supersonic diffuser and different boundary-layer bleed schedules. The computed results are compared with detailed experimental data for the ramp and cowl surface pressure distribution, and the boundary-layer pitot profiles at seven different streamwise locations. The agreement with the experimental results is generally good, although the experimental data display evidence of three dimensionality over a portion of the inlet flowfield.

Original languageEnglish (US)
Pages (from-to)172-179
Number of pages8
JournalAIAA journal
Issue number2
StatePublished - Feb 1981

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering


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