Accession Number:

AD0258243

Title:

INVESTIGATION OF THE FLOW OVER AN AXISYMMETRIC COMPRESSION SURFACE AT HIGH MACH NUMBERS

Descriptive Note:

Corporate Author:

NAVAL ORDNANCE LAB WHITE OAK MD

Personal Author(s):

• LANKFORD,J.L.

Report Date:

1961-05-01

Pagination or Media Count:

19.0

Abstract:

Axisymmetric compression surfaces designed for Mach number 7 were fired as projectiles in the NOL pressurized ballistics range no. 3. Range pressures varied from approximately 100 to 300 mm of mercury with a few firings at 1 atmosphere. Range temperature was the ambient or room temperature. Mach numbers from 4.5 to 7.4 were recorded. Results are presented in the form of spark photographs from which data on flow fields and boundary-layer conditions were obtained. The data are analyzed and compared with theory. Although the wall temperatures are too low for simulation of a flight case and the boundary layer appears laminar, the results are of general interest because they represent conditions with a thin boundary layer on a cold surface. A strong effect of wall temperature on separation is noted. Author

Descriptors:

• *HYPERSONIC CHARACTERISTICS
• *PROJECTILES
• *SUPERSONIC FLOW
• AERODYNAMIC CHARACTERISTICS
• AERODYNAMIC CONFIGURATIONS
• BODIES OF REVOLUTION
• BOUNDARY LAYER
• SENSES(PHYSIOLOGY)
• TEMPERATURE

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE