Rocket Propulsion Thrust Coefficient, Characteristic ...
• Ideal thrust coefficient is only function of – , (=A e /A t), p a /p o –recall p e /p o = fn( ) • Note: c fn(T o, MW) • Thrust coeff. depends mostly on pressure distribution in thrust chamber –from normalizing thrust by p o A t Ideal Thrust Coefficient t e o a o e o e ideal A A p p p p p p c 1 1 1, 1 1 2 1 2 a nozzle ...
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Rocket Nozzle Geometries - gatech.edu
seitzman.gatech.edufor 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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