Accession Number:

AD0609458

Title:

PRESSURE MEASUREMENTS FOR MACH 8 FLOWS OVER EXPANSION CORNERS AND RAMPS ON AN INTERNALLY COOLED MODEL. PART II. FLOWS OVER A FLAT PLATE WITH AND WITHOUT A PARTIAL SPAN RAMP. PART OF AN INVESTIGATION OF HYPERSONIC FLOW SEPARATION AND CONTROL CHARACTERISTICS.

Descriptive Note:

Corporate Author:

GRUMMAN AIRCRAFT ENGINEERING CORP BETHPAGE NY

Personal Author(s):

Report Date:

1964-10-01

Pagination or Media Count:

184.0

Abstract:

Pressure distributions were obtained for Mach 8 flows over a sharp 40 degree expansion corner and ahead of ramps on an internally cooled model. Full and partial span ramps, having wedge angles up to 30 degrees, were tested at model angles of attack from -45 to 10 degrees for Reynolds numbers ranging from 1.1 to 3.3 million. The model wall temperature was maintained at fairly constant levels ranging from 450 to 1150 degrees Rankine.

Subject Categories:

  • Aircraft
  • Test Facilities, Equipment and Methods
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE