Accession Number : AD0774386

Title :   Hypersonic Flow over a Flat Plate.

Descriptive Note : Master's thesis,

Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING

Personal Author(s) : Tuck,William M. , Jr

Report Date : NOV 1973

Pagination or Media Count : 82

Abstract : The purpose of the study was to determine the performance of the AFIT hypersonic shock tunnel and to demonstrate the use of heat transfer gages and miniature pressure transducers in the facility by analyzing the flow over a flat plate model. The performance of the tunnel was determined by calibrating the driven tube and test section. Calibration of the driven tube consisted of measuring driven shock speed, pressure ratio across the driven shock, and pressure after shock reflection. The data obtained were then plotted as a set of performance curves. The test section performance was determined from an impact rake survey of the nozzle exit. The Mach number of the flow was found to be 11.10 and the diameter of the nozzle inviscid core nominally 18 in. (Modified author abstract)

Descriptors :   *Flat plate models, *Hypersonic flow, Shock tunnels, Calibration, Heat transfer, Pressure, Transducers, Theses

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE