NONEQUILIBRIUM HYPERSONIC STAGNATION FLOW AT LOW REYNOLDS NUMBERS,
Abstract
An analysis of nonequilibrium-dissociated stagnation point flow on highly cooled blunt bodies in a hypersonic stream of air or diatomic gas at low Reynolds numbers is presented. An arbitrary atom recombination rate on the surface is allowed. With the use of a continuum, thin shock layer model, it is shown that for flight speeds on the order of 25,000 ft/sec or less, the problem can be broken down into two regimes, both of which can be treated analytically with good approximation. The first is a generalized nonequilibrium vorticity-interaction flow regime where most of the significant gas phase reaction effects occur, including the transition from recombination rate to dissociation rate-controlled behavior. The closed form solutions given for this regime predict atom concentrations and nonequilibrium heat transfer within 10 percent of exact numerical solutions down to shock layer Reynolds numbers of roughly 100. The second and lower Reynolds number regime embraces fully viscous shock layer flow with appreciable nonadiabatic shock slip effects; here an analytical solution is given by treating the flow as nearly chemically frozen throughout. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 03, 1964
- Accession Number
- AD0607215
Entities
People
- G. I. Inger
Organizations
- The Aerospace Corporation