Accession Number : AD0425543

Title :   DATA REPORT: AEDC TUNNEL C, BOEING TEST NO. 010, SURFACE ROUGHNESS HEAT TRANSFER AND PRESSURE TEST ON MODEL AD-633M-2,

Corporate Author : BOEING CO SEATTLE WASH

Personal Author(s) : Ayling,D. L.

Report Date : 26 NOV 1963

Pagination or Media Count : 1

Abstract : Heat transfer and pressure data were obtained from a series of flat plates with various wave configurations representing surface roughness, at angles of attack from -5 to +10 degrees. Boundary layer data includes the probe pressure temperature readings from 3 thermocouples mounted on the model and the vertical probe position. The centerline of the probe was .020 inch from the model surface when the probe position is zero. The Mach 10 tunnel, Tunnel C, is an axi-symmetric continuous flow, variable density, hypersonic wind tunnel with a 50-inch diameter test section. Because of changes in boundary layer thickness caused by changing pressure level, the Mach 10 contoured nozzle produces an average test section Mach number which varies from 10.0 at a stagnation pressure of 200 psia to 10.2 at 1800 psia. The centerline flow distribution is uniform about 0.5% in Mach number. There is a slight axial gradient on the order of 0.01 Mach number per foot. A hydraulically driven angle of attack mechanism pitches the model in a vertical plane from -15 to +15 degrees. The remotely controlled, water-cooled roll mechanism is electrically driven and is capable of rotating the model sting combination + or - 180 degress. The tests were performed at Po=340 and 1640 psia, and To=1256 and 1426 F respectively at a nominal freestream Reynolds number per foot of 0.5 and 2.0 x 106. (Author)

Descriptors :   *BOOST GLIDE VEHICLES, ANGLE OF ATTACK, BOUNDARY LAYER, HEAT TRANSFER, HYPERSONIC CHARACTERISTICS, MODEL TESTS, PRESSURE, ROUGHNESS, SURFACE PROPERTIES, SURFACES, TABLES(DATA), WIND TUNNEL MODELS

Distribution Statement : APPROVED FOR PUBLIC RELEASE