Accession Number : AD0838727

Title :   TEST REPORT FOR PHASE III OF THE AERODYNAMIC HEATING TEST AT THE NASA LANGLEY UNITARY PLAN WIND TUNNEL,

Corporate Author : GENERAL DYNAMICS SAN DIEGO CA CONVAIR DIV

Personal Author(s) : Yip, P. S.

Report Date : 02 JUL 1959

Pagination or Media Count : 445

Abstract : The primary purpose of the test was to determine the effect of variously shaped protuberances on the convective heat transfer coefficients for a flat plate in turbulent supersonic flow. The secondary objective of the test was to determine the convective heat transfer coefficients for the surfaces of the protuberance models. The model configurations tested were the plain flat plate, 2 in. x 4 in. flange, 30 deg. wedge 1/4 cylinder, 1 in. x 2 in. flange, 2.8 in. D swept cylinders, and 2.8 in. D vertical cylinders. (Author)

Descriptors :   (*AIRFRAMES, EXTENDABLE STRUCTURES), (*EXTENDABLE STRUCTURES, AERODYNAMIC HEATING), SUPERSONIC CHARACTERISTICS, FLOW FIELDS, WEDGES, FLAT PLATE MODELS, CYLINDRICAL BODIES, FLANGES, HEAT TRANSFER, TEST METHODS, WIND TUNNEL MODELS, MODEL TESTS, FLOW VISUALIZATION, REYNOLDS NUMBER, BLUNT BODIES, SURFACE PROPERTIES, BOUNDARY LAYER.

Subject Categories : Aircraft
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE