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Rocket Nozzle Geometries - gatech.edu

1 Nozzle Geometries -1 Copyright 2012, 2018 by Jerry M. Seitzman. All rights Rocket PropulsionNozzle GeometriesNozzle ConfigurationsNozzle Geometries -2 Copyright 2012, 2018 by Jerry M. Seitzman. All rights Rocket PropulsionNozzle Configurations So far considered 1-d ideal nozzles primarily for over/underexpandedoperation Described one real effect flow separation Continue by looking at real Nozzle configurations ( Nozzle geometry) Converging section subsonic flow, favorable pressure gradient can use almost any shapewith minimal poloss Diverging section design goals high Isp, low Nozzle mass and length ConvergingDivergingThroat2 Nozzle Geometries -3 Copyright 2012, 2018 by Jerry M.

for wall boundary layers) –must account for variable speed of sound • Approximate optimization method of Rao –initial (near throat) section spherical –transition to parabola Rao, Jet Propulsion 28, pp. 377-382 (1958) Rao, J. Amer. Rocket Soc. 31, pp. 1488-1494 (1961) Allman and Hoffman, AIAA J. 19, pp. 750-751 (1981)

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