Accession Number:

AD0258436

Title:

AN INVESTIGATION OF LAMINAR HEAT TRANSFER TO SLENDER CONES IN THE HYPERSONIC SHOCK TUNNEL

Descriptive Note:

Corporate Author:

CORNELL AERONAUTICAL LAB INC BUFFALO NY

Personal Author(s):

• WITTLIFF, CHARLES E.
• WILSON, MERLE R.

Report Date:

1961-05-01

Pagination or Media Count:

71.0

Abstract:

An investigation of laminar heat transfer to slender yawed cones was conducted in the CAL 11 by 15-in. shock tunnel at Mach numbers from 11 to 13 and at yaw angles up to 14 degrees. Both sharp and blunt-nose cones having a 5- degree half angle were tested. The heat-transfer rates are compared with theoretical predictions. The effects on the local heat-transfer rates of the boundary-layer displacement thickness, transverse curvature, yaw, nose bluntness, and the entropy sublayer are discussed. At zero yaw, the experimental data for the sharp cone are in good agreement with theory when boundary-layer displacement and transverse-curvature effects are included. At larger than 3 degree yaw angles, the experimental heat transfer was found to be greater than that predicted theoretically. However, at these yaw angles the heat-transfer distribution on the windward side was in good agreement with laminar boundary-layer calculations based on an assumption of local similarity.

Descriptors:

• *HEAT TRANSFER
• *CONICAL BODIES
• HYPERSONIC WIND TUNNELS
• HYPERSONIC FLOW
• LAMINAR BOUNDARY LAYER
• YAW
• HYPERSONIC VEHICLES

Subject Categories:

• Thermodynamics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE