Analysis for design of axisymmetric rocket motor nozzles is based upon assumptions for reacting flows; method is presented for employing results to determine whether or not given nozzle contour is actually optimum contour; results of analysis are set of partial differential equations for determining Lagrange multipliers and set of algebraic equations for determining initial conditions for these multipliers on boundaries of region.
General method for determining optimum thrust nozzle contours for chemically reacting gas flows
AIAA J
AIAA Journal ; 5 , n 4
1967
7 pages
Aufsatz (Zeitschrift)
Englisch
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