Shock Enhancement and Control of Hypersonic Combustion.
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
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 06, 1994
- Accession Number
- ADA299492
Entities
People
- Edward E. Zukoski
- Frank E. Marble
Organizations
- California Institute of Technology