SELF-MODELING PROBLEMS OF FLOW OF A COMBUSTIBLE GAS MIXTURE AROUND BODIES,
Abstract
The supersonic, steady-state flow of combustible mixtures in which detonation or combustion fronts are formed is of interest for supersonic combustion, for the use of steady-state detonation waves in some technological processes, and also for studying high temperature reaction kinetics. In the present study, a theoretical analysis is presented for one-dimensional or axisymmetrical supersonic flows of combustible gas mixtures over a cone, wedge or along a curved wall. New solutions were presented for a flow involving the formation of an adiabatic compression shock followed by a deflagration front. Flows over a wedge or cone with point or linear ignition sources generating deflagration fronts were also analyzed. In addition the degeneration of a detonation wave into an adiabatic shock and a combustion front was considered. In all cases, the detonation and combustion fronts were considered to have zero thickness, and it was assumed that the gas is ideal and that the specific heat on both sides of the shock is constant. The solutions are presented in the form of shock and detonation polars on u vs v diagrams (u and v are the velocity components after the shock). (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 11, 1967
- Accession Number
- AD0666149
Entities
People
- G. G. Chernyi
Organizations
- National Air and Space Intelligence Center