Methods for Distinguishing Type of Hypersonic Boundary Layer in Shock Tunnel.

摘要: Abstract : An experimental program for studying the transition phenomenon, boundary layer characteristics, and local heat transfer rates on 4- 8-foot long 10 deg included angle cones in a hypersonic chock tunnel has brought about development improvement of instrumentation methods distinguishing laminar, transition, turbulent layers relatively short test time facilities. The used include schlieren optics, from thin-film sputtered platinum surface gauges, surveys through using impact pressure, total temperature, thin wedges. Also, actual oscilloscope traces, directly instrumentation, be to define type layer. (Author)