Accession Number:

ADA014240

Title:

Separation Ahead of Controls on Swept Wings.

Descriptive Note:

Interim rept. Apr 73-Apr 75,

Corporate Author:

AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OHIO

Report Date:

1975-06-01

Pagination or Media Count:

53.0

Abstract:

Shock-induced flow-separation ahead of trailing edge controls on swept wings is investigated with emphasis on the effects of boundary layer transition on the location and shape of the separation line. Experimental results were obtained by using forward facing steps mounted on swept-leading-edge flat-plate wing models in the ARL Mach 6 Tunnel for model running length Reynolds numbers varying from 0.9 to 33 million. The data support qualitatively a proposed, strip-type method for estimating, the extent and shape of the three dimensional region of separated flow ahead of controls on swept wings. Author

Subject Categories:

  • Aircraft
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE