Engineering topics
Publications and source records attributed to White, R. E..
A theory is presented that makes it possible to apply one-dimensional techniques to compressible striated nozzle flow with small radius of curvature ratio throats. The throat plane solution is shown to approximate the two-dimensional axisymmetric flowfield and can be used for analyzing the throat plane in converging-diverging type nozzles with striated flow for radius of curvature throat ratios down to 0.25.
An analytical method was developed which is capable of estimating the chamber and throat conditions in a nozzle with a low radius of curvature throat. The method was programmed using standard FORTRAN 4 language and includes chemical equilibrium calculation subprograms (modified NASA Lewis program CEC71) as an integral part. The method determines detailed and gross rocket characteristics in the presence of striated flows and gives detailed results for the motor chamber and throat plane with as many as 20 discrete zones. The method employs a simultaneous solution of the mass, momentum, and energy equations and allows propellant types, 0/F ratios, propellant distribution, nozzle geometry, and injection schemes to be varied so to predict spatial velocity, density, pressure, and other thermodynamic variable distributions in the chamber as well as the throat. Results for small radius of curvature have shown good comparison to experimental results. Both gaseous and liquid injection may be considered with frozen or equilibrium flow calculations.