Accession Number : ADA299492
Title : Shock Enhancement and Control of Hypersonic Combustion.
Descriptive Note : Final rept. 15 Nov 89-30 Sep 94,
Corporate Author : CALIFORNIA INST OF TECH PASADENA
Personal Author(s) : Marble, Frank E. ; Zukoski, Edward E.
PDF Url : ADA299492
Report Date : 06 DEC 1994
Pagination or Media Count : 51
Abstract : It is proposed to enhance the rate of mixing and combustion of hydrogen and air, and thereby reduce combustor length of scramjet combustors, through the introduction of stream wise vorticity generated by the interaction of a weak oblique shock wave with the density gradient between air and a cylindrical jet of hydrogen. Because of the high Mach number flow the combustor, the oblique shock traverses the jet a very small angle and the principle of slender body theory allows one to replace the three-dimensional steady flow with a two-dimensional unsteady flow. As a consequence, two-dimensional time-dependent computational studies and an extensive experimental shock tube investigation were employed to assess mixing rates for the steady flow in the combustor. The results indicated that under realistic conditions, adequate mixing could be accomplished within one millisecond. jg p.1
Descriptors : *COMBUSTION, *SHOCK, *HYPERSONIC CHARACTERISTICS, CONTROL, ANGLES, DENSITY, OPTIMIZATION, COMPUTATIONS, SLENDER BODIES, HIGH RATE, TIME DEPENDENCE, TWO DIMENSIONAL, SHOCK WAVES, RATES, VORTICES, HYDROGEN, COMBUSTORS, CYLINDRICAL BODIES, LENGTH, MIXING, FLOW, MACH NUMBER, TWO DIMENSIONAL FLOW, UNSTEADY FLOW, SUPERSONIC COMBUSTION RAMJET ENGINES, GRADIENTS, SHOCK TUBES, STEADY FLOW, THREE DIMENSIONAL FLOW, LOW INTENSITY.
Subject Categories : Electric and Ion Propulsion
Distribution Statement : APPROVED FOR PUBLIC RELEASE