Summary: JOURNAL OF THERMOPHYSICS AND HEAT TRANSFER
Vol. 16, No. 1, January­March 2002
Numerical Simulation of High-Temperature
Gas Flows in a Millimeter-Scale Thruster
A. A. Alexeenko¤
and D. A. Levin
Pennsylvania State University, University Park, Pennsylvania 16802
S. F. Gimelshein
George Washington University, Washington, D.C. 20052
R. J. Collins§
University of Minnesota, Minneapolis, Minnesota 55455
and
G. N. Markelov¶
Institute of Theoretical and Applied Mechanics, 630090, Novosibirsk, Russia
High-temperature nozzle ows at low Reynoldsnumbers are studied numerically by the direct simulationMonte
Carlo method. Modeling results are compared with the experimental data on the speci c impulse ef ciency of a
heated nitrogen ow at Re = 1:78 ££ 102 ­4:09 ££ 102. Good agreement between modelingand data was observed for
nonadiabatic wall conditions. The relative in uence of three major thrust loss factors-- ow divergence, surface
friction, and heat transfer in axisymmetric and three-dimensional nozzles--is estimated for stagnation tempera-
tures of 300, 1000, and 2000 K and Re = 2:05 ££ 102. For a stagnation temperature of 1000 K, the speci c impulse

Source: Alexeenko, Alina - School of Aeronautics and Astronautics, Purdue University

Collections: Engineering