Accession Number : AD0274583

Title :   HEAT TRANSFER TO 0 DEGREE AND 75 DEGREES SWEPT BLUNT LEADING EDGES IN FREE FLIGHT AT MACH NUMBERS FROM 1.90 TO 3.07

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s) : O'NEAL,ROBERT L. ; BOND,ALECK C.

Report Date : APR 1962

Pagination or Media Count : 1

Abstract : A flight investigation of a rocket-powered model was conducted to study the heat transfer to wing leading edges in the vicinity of their juncture with a cylindrical body. Heat-transfer data were obtained on leading edges of 3/4-inch diameter at sweep angles of 0 and 75 degrees, Mach numbers from 1.90 to 3.07, and Reynolds numbers based on leading-edge diameter from 8.05 to 11.80 times 10 to the 5th power. The measured heating rates of both the 0 and 75 degrees swept leading edges were of the magnitude predicted by turbulent theory rather than by laminar theory. It is believed that the high level of heating observed on the leading edges was due to the influence of conditions existing in the turbulent boundary layer of the body. Comparison of the average measured heating on the cylindrical portions of both the swept and unswept leading edges indicates that the heating of the unswept segment was generally about twice that of the swept segment. (Author)

Descriptors :   *AERODYNAMIC HEATING, *CYLINDRICAL BODIES, *WING BODY CONFIGURATIONS, BODIES OF REVOLUTION, HYPERSONIC CHARACTERISTICS, MODEL TESTS, SUPERSONIC FLOW, SWEPT WINGS, WIND TUNNEL MODELS

Distribution Statement : APPROVED FOR PUBLIC RELEASE