1970•NASA STI Repository (National Aeronautics and Space Administration)Open access

Digital program analyzes supersonic flow field within bell-shaped rocket nozzles

J. J. Elliott, R. R. Stromsta

Abstract

Digital computer program computes and analyzes supersonic flow field in axisymmetric rocket nozzle for specified gas properties, nozzle geometry, and input or starting line. Method of characteristics is used for solution of set of hyperbolic partial differential equations.

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Available abstract

Key concepts: Nozzle, Supersonic speed, Rocket (weapon), Choked flow, Rotational symmetry, Partial differential equation, Digital computer, Aerospace engineering