CALCULATIONS FOR AIR FLOWS IN DISSOCIATION EQUILIBRIUM
ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
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Results of calculations carried out for a model of air in dissociation equilibrium are presented in graphical form. The quantities computed are 1 flow variables including species concentrations behind normal and oblique shock waves, 2 flow variables in axisymmetric conical flow fields, 3 stagnation point values of flow variables on the stagnation streamline behind two-dimensional and axisymmetric detached shock waves, and 4 flow variable gradients at the shock wave on stagnation streamlines. Computations are given for free stream temperatures of 273.16K and 300K, free stream pressures of 1.0, .1, .01, .001, and .0001 atmospheres, and a range of initial Mach numbers and cone angles to provide flow field temperatures in the range 3000K - 10,000K. Brief derivations of the equations employed are given. The present calculations are oriented toward application in experiments in hypersonic flow with ground facilities such as shock tubes and ballistic ranges. In addition, they furnish important supplementary information to theoretical studies of nonequilibrium flows.
- Fluid Mechanics