NASA NTRS · 19660057308
A general method for determining optimum thrust nozzle contours for gas-particle flows.
Abstract
Optimization analysis for axisymmetric rocket motor nozzle design based on assumptions for gas particle flow
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Hoffman, J. D., Thompson, H. D.. 1966-06-01. A general method for determining optimum thrust nozzle contours for gas-particle flows.. https://ntrs.nasa.gov/citations/19660057308
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