Accession Number:

ADA361146

Title:

Effect of Sideslip on the Flow over a 65-deg Delta Wing

Descriptive Note:

Final rept.

Corporate Author:

DELFT UNIV OF TECHNOLOGY (NETHERLANDS)DEPT OF AEROSPACE ENGINEERING

Personal Author(s):

Report Date:

1999-01-01

Pagination or Media Count:

61.0

Abstract:

Flow-visualization tests, surface-pressure measurements and balance tests were conducted on a model of a flat-plate 65-deg swept delta wing in a low-speed wind tunnel. The model was tested at a fixed angle of attack of 30 deg and at angles of sideslip up to 20 deg. The tests generated data that were used to study the effect of sideslip on the flow over the delta wing.

Subject Categories:

  • Aerodynamics
  • Attack and Fighter Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE