Monte Carlo Direct Simulation of Axisymmetric Rarefied Gas Flows Through Thruster Nozzles for Spacecrafts 912062
Axial symmetric flows of a mono-atomic rarefied gas exhausted through the thruster nozzle of an artificial satellite were numerically simulated by the Direct Simulation Monte Carlo method, since the transitional flow regime occurs at altitudes where the enhancement region is several orders of magnitude larger than the nozzle throat diameter of the thruster (high altitude rocket).
On macroscopic flows in the nozzle or the orifice, the effects of Knudsen numbers are revealed. At lower Knudsen number regions, the flows are more accelerated by the effects of inter-molecular collisions. On the inside surface of the nozzle, macroscopic velocity and temperature distributions are built up in the radial direction. At lower Knudsen number regions, the thickness of these boundary layers are getting thinner.
Citation: Ota, M. and Tanaka, T., "Monte Carlo Direct Simulation of Axisymmetric Rarefied Gas Flows Through Thruster Nozzles for Spacecrafts," SAE Technical Paper 912062, 1991, https://doi.org/10.4271/912062. Download Citation
Author(s):
Masahiro Ota, Tetsuya Tanaka
Affiliated:
Department of Mechanical Engrg., Tokyo Metropolitan University, Tokyo, Japan
Pages: 7
Event:
International Pacific Air & Space Technolgy Conference
ISSN:
0148-7191
e-ISSN:
2688-3627
Also in:
International Pacific Air and Space Technology Conference and 29th Aircraft Symposium Proceedings-P-246
Related Topics:
Nozzles
Satellites
Gases
Simulation and modeling
Logistics
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