Numerical study of low pressure nuclear thermal rocketsThe flowfields and performance of low pressure nuclear thermal rockets, which use hydrogen as a propellant, are studied by solving the Navier-Stokes equations and the species equations. A finite-rate chemistry model is used in the species equations, and the turbulence is simulated by the Baldwin-Lomax turbulence model with a modified van Driest's damping constant. The calculated results for the chamber temperatures of 3200 K and 4000 K with a chamber pressure range of 0.1 atm to 6 atm are presented as contours, centerline variations, and exit profiles. The performance values from the present calculations, such as the vacuum specific impulse and thrust, are compared with those from the 1D, inviscid equilibrium and frozen flow code.
Document ID
19920071558
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kim, Suk C. (Sverdrup Technology, Inc.; NASA, Lewis Research Center Cleveland, OH, United States)
Stubbs, Robert M. (NASA Lewis Research Center Cleveland, OH, United States)