SEPARATED FLOW OVER A BODY OF REVOLUTION

The technique uses the computer to integrate various solutions and solution properties of the sub-flowfields which make up the entire flowfield without resorting to a finite difference solution to the complete Navier-Stokes equations. The technique uses the unsteady cross flow analogy and a new solution to the required two-dimensional unsteady separated flow problem based upon an unsteady discrete-vorticity wake. Data for the forces and moments on bodies of revolution at high angle of attack (outside the range of linear inviscid theories) such that the flow is substantially separated are produced which compare well with experimental data at low speeds. In addition, three- dimensional steady separation regions and wake vortex patterns are determined.

• Availability:
  • Find a library where document is available. Order URL: http://worldcat.org/issn/00218669
• Corporate Authors:

  American Institute of Aeronautics and Astronautics

  1290 Avenue of the Americas
  New York, NY  United States  10019
• Authors:
  • Marshall, F J
  • Deffenbaugh, F D
• Publication Date: 1975-2

Media Info

• Features: References;
• Pagination: p. 78-85
• Serial:
  • Journal of Aircraft
  • Volume: 12
  • Issue Number: 2
  • Publisher: American Institute of Aeronautics and Astronautics
  • ISSN: 0021-8669
  • Serial URL: https://arc.aiaa.org/journal/ja

Subject/Index Terms

• TRT Terms: Bodies of revolution; Boundary layer separation; Flow; Unsteady flow
• Old TRIS Terms: Separated flow
• Subject Areas: Design; Marine Transportation;

Filing Info

• Accession Number: 00099460
• Record Type: Publication
• Source Agency: Engineering Index
• Files: TRIS
• Created Date: Sep 30 1975 12:00AM