Accession Number:

AD0749934

Title:

Experimental Surface Pressure Distributions on Three Bodies of Revolution at Mach Numbers from 0.7 to 2.02

Descriptive Note:

Corporate Author:

NAVAL WEAPONS CENTER CHINA LAKE CA

Personal Author(s):

Report Date:

1972-08-01

Pagination or Media Count:

136.0

Abstract:

Wind tunnel tests were conducted to measure surface pressure distributions on three bodies of revolution at Mach numbers from 0.7 to 2.02 and angle of attack from 10 to -10 degrees. The three bodies were based on the same ogive-cylinder, with one having a sharp nose and the other two being spherically tipped. Surface pressure distributions are presented, along with expressions relating the flow angle to the pressure difference across the spherical nose caps.

Subject Categories:

  • Aerodynamics
  • Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE