ADVANCED AIR-BREATHING ENGINE STUDY.
Abstract
A summary of progress in the analytic studies of the exhaust nozzles, and turbulent jet theory for application to supersonic combustion ramjets are reported. The performance of nozzles with supersonic entrance velocities have been computed. Contours were chosen to satisfy the optimization criteria of Rao. Corrections on contour and thrust were made for a turbulent boundary layer. Kinetic energy conversion efficiency of about 86 was computed for the minimum length optimum nozzle. Computed wall friction coefficients were found to be well correlated if one assumes a constant incompressible friction coefficient evaluated at the nozzle entrance and the correcting for the Mach number along the wall. Since an exact transformation of the compressible turbulent boundary layer equations to an analogous incompressible problem is not possible with current formulations of the eddy viscosity term, a transformation which satisfies an integral equation has been effected. The Howarth transformation is used for the normal coordinate and a new transformation is proposed for the lengthwise coordinate. Comparison is made of turbulent diffusion flame length predictions for various theories of eddy viscosity. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 15, 1964
- Accession Number
- AD0349675
Entities
People
- D. Seiveno
- J. Tromblay
- R. Kushida