Accession Number : AD0700143

Title :   SUPERSONIC COMBUSTION RESEARCH TECHNIQUES IN A HYPERSONIC SHOCK TUNNEL.

Descriptive Note : Final rept.,

Corporate Author : SHEFFIELD UNIV (ENGLAND) DEPT OF FUEL TECHNOLOGY AND CHEMICAL ENGINEERING

Personal Author(s) : Parsons,Raymond John

Report Date : MAR 1969

Pagination or Media Count : 270

Abstract : The report is concerned with the use of a hypersonic shock tunnel in the simulation of combustor conditions at flight Mach numbers in excess of 10, with particular relevance to instrumentation techniques. The use of combustion heated helium as driver gas was shown to correctly simulate combustor conditions from Mach 10 to Mach 16. The starting transients in supersonic ducts were examined to establish criteria for minimizing the starting time and the overpressure. These are achieved by evacuating the duct to between 1/10th and 1/30th of the running static pressure. The electromagnetic induction method of measuring gas velocity proved to be a novel and acceptable instrumentation technique previously unused on shock tunnel test sections. A rapidly responding estimation of mean velocity is obtained. The velocity meter together with pressure and temperature measurements is now being used to analyze the performance of an aerofoil injector which was designed specifically to promote supersonic turbulence. (Author)

Descriptors :   (*SUPERSONIC COMBUSTION, SIMULATION), SHOCK TUBES, HYPERSONIC CHARACTERISTICS, INSTRUMENTATION, TEST METHODS, DUCTS, VELOCITY, ELECTROMAGNETIC FIELDS, INDUCTANCE, AIRFOILS, INJECTORS, THESES, GREAT BRITAIN

Subject Categories : Test Facilities, Equipment and Methods
      Combustion and Ignition

Distribution Statement : APPROVED FOR PUBLIC RELEASE