Accession Number:

AD0755694

Title:

An Experimental Investigation of the Laminar Boundary Layer on a Spinning Ogive Cylinder in Supersonic Flow,

Descriptive Note:

Corporate Author:

NAVAL ORDNANCE LAB WHITE OAK MD

Report Date:

1972-11-01

Pagination or Media Count:

133.0

Abstract:

Pitot pressure surveys were made of the laminar boundary layer on an ogive-cylinder model at Mach 3.02 and 4.10. Surveys were made at five stations along the model, at angles of attack of zero and four degrees, with and without spin. Tests with spin were performed at Mach 3.02. The pitot pressure data has been used to compute boundary-layer velocity profiles, and results from two data-reduction procedures are presented. Some comparisons are made with theoretical velocity profiles for the zero spin, zero angle-of-attack case. Author

Subject Categories:

  • Ammunition and Explosives
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE