Accession Number:

ADA139408

Title:

Boundary Layer Trip Performance Test on a 7-deg Cone Model at Mach Number 8

Descriptive Note:

Final rept. 1-6 Sep 1983

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

• Coulter, S. M.
• Simons, S. A.

Report Date:

1983-10-01

Pagination or Media Count:

52.0

Abstract:

This study was performed to obtain additional knowledge of the physical characteristics and occurrences within a tripped boundary layer as well as determining suitable techniques for the measurement of these characteristics. A sharp, 7-deg half-angle cone model was tested in Mach 8 flow conditions at free-stream unit Reynolds numbers of 1.3- and 2.6-million per foot at zero angle of attack. Boundary layer surveys pitot and total temperature, coax heat-gage, and model pressure data were acquired for comparison of a variety of boundary layer trip geometries.

Descriptors:

• *BOUNDARY LAYER TRANSITION
• *HYPERSONIC FLOW
• *TURBULENT FLOW
• BOUNDARY LAYER FLOW
• FLOW FIELDS
• HEAT TRANSFER
• HYPERSONIC WIND TUNNELS
• NOSE CONES
• PRESSURE MEASUREMENT
• REYNOLDS NUMBER
• SHARP BODIES

Subject Categories:

• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE