Hypersonic Flow over a Flat Plate.
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1973
- Accession Number
- AD0774386
Entities
People
- William M. Tuck Jr
Organizations
- Air Force Institute of Technology