NASA NTRS · 19700000578
Digital program analyzes supersonic flow field within bell-shaped rocket nozzles
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.
Keep this discovery
Explore connections, maps & timelines
Elliott, J. J., Stromsta, R. R.. 1970-11-01. Digital program analyzes supersonic flow field within bell-shaped rocket nozzles. https://ntrs.nasa.gov/citations/19700000578
Cite the original work for its findings. Save a collection to share your selection of sources.