PREDICTION OF BOUNDARY-LAYER FLOW SEPARATION IN V/STOL ENGINE INLETS

The paper provides a theoretical description of the development of the boundary layer on the lip and diffuser surface of a subsonic inlet at arbitrary operating conditions of mass flow rate, freestream velocity, and incident angle. Both laminar separation on the lip and turbulent separation in the diffuser are discussed. The agreement of the theoretical results with model experimental data illustrates the capability of the theory to predict separation location. The effects of throat Mach number, inlet size, and surface roughness on boundary-layer development and separation are illustrated.

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  • Corporate Authors:

    American Institute of Aeronautics and Astronautics

    1290 Avenue of the Americas
    New York, NY  United States  10019
  • Authors:
    • Chou, D C
    • Luidens, R W
    • Stockman, N O
  • Publication Date: 1978-8

Media Info

  • Features: References;
  • Pagination: p. 474-481
  • Serial:
    • Journal of Aircraft
    • Volume: 15
    • Issue Number: 8
    • Publisher: American Institute of Aeronautics and Astronautics
    • ISSN: 0021-8669

Subject/Index Terms

Filing Info

  • Accession Number: 00188612
  • Record Type: Publication
  • Source Agency: Engineering Index
  • Files: TRIS
  • Created Date: Mar 14 1979 12:00AM