Accession Number:

AD0869314

Title:

Results of Supersonic Heat-Transfer Studies on Blunt Swept Leading Edges.

Descriptive Note:

Aerodynamic investigative study 1967-1968,

Corporate Author:

MASSACHUSETTS INST OF TECH CAMBRIDGE AEROPHYSICS LAB

Personal Author(s):

• Gollnick,Albert F. , Jr

Report Date:

1970-03-01

Pagination or Media Count:

58.0

Abstract:

Stagnation-line heat-transfer distributions were obtained on blunt swept leading edges at Mach 3.66 and a Reynolds number per foot of 210,000. Pressure distributions were obtained for comparable test conditions. The results illustrate the effects of various flow nonuniformities on leading-edge heat transfer and pressure, including those arising from finite span and nonuniform leading-edge sweep free-stream nonuniformity induced by the bow shock of typical blunt body boundary-layer interaction near the leading-edge root and impingement of a trailing-tip vortex. None of these effects can be predicted analytically as yet, and all may lead to significant deviation from the levels based on infinite-cylinder theory. The importance of the individual results are discussed, and, where possible, appropriate design criteria are presented. Author

Descriptors:

• (*AIR TO AIR MISSILES
• HEAT TRANSFER)
• (*LEADING EDGES
• SUPERSONIC CHARACTERISTICS)
• BLUNT BODIES
• AIRCRAFT
• AERODYNAMIC HEATING
• PRESSURE
• STAGNATION POINT
• REYNOLDS NUMBER
• SHOCK WAVES
• BOUNDARY LAYER
• VORTICES

Subject Categories:

• Aircraft
• Air- and Space-Launched Guided Missiles
• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE