Thrust Nozzle Optimization for Non-Equilibrium, Chemically Reacting Flows Including Boundary Layer Effects.
Technical rept. 1 Sep 66-31 Jan 69,
PURDUE UNIV LAFAYETTE IN JET PROPULSION CENTER
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An optimization analysis and a method for the application of the results are presented for the design of axisymmetric or two-dimensional optimum thrust nozzles for non-equilibrium chemically reacting flows including boundary layer effects. The analysis is based on the usual assumptions applicable to non-equilibrium, chemically reacting flows, and on the assumption that the boundary layer is thin. The problem is formulated to maximize the pressure thrust integral along the supersonic wall contour for a general isoperimetric design constraint. The results of the optimization analysis are a set of hyperbolic partial differential equations for determining the Lagrange multipliers of the optimization problem in the region of interest, and a set of algebraic equations for determining the initial and boundary conditions for these multipliers on the boundaries of the region. Two special cases of the general results for non-equilibrium, chemically reacting flows are presented. These are 1 flow of a simple dissociating gas, and 2 equilibrium or frozen flow of a general gas mixture. Nozzle design schemes for these two special cases are derived by appropriate reduction of the results for the general case. Numerical schemes for these special cases are discussed. Author
- Fluid Mechanics