Numerical study of flow structure and thrust performance for 3-D MEMS-based nozzles

A. A. Alexeenko, D. A. Levin, S. F. Girnelshein'l, R. J. Collins, B. D. Reed

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

A 3-D flow in a MEMS-based micronozzle has been modeled using the DSMC method. Two potential propellant selections: a solid mono-propellant LAX112 and a hydrogen-air mixture, have been compared at stagnation pressures 0.1 and 1 atm. The corresponding Reynolds number of the flow varies from 30 to 440. For both pressure and propellant conditions, the flow is strongly influenced by the friction and heat transfer losses. The calculated specific impulse is about 170 sec for a stagnation pressure of 1 atm and about 120 sec for 0.1 atm. The discharge coefficient varies from 0.86 to 0.97 depending on the Reynolds number. The calculated infrared spectra for the LAX112 propellant suggest that the infrared signal from such plumes can be detected and used to determine the influence of the cold wall boundary layer on the flow parameters at the nozzle exit.

Original languageEnglish (US)
Title of host publication32nd AIAA Fluid Dynamics Conference and Exhibit
StatePublished - Dec 1 2002
Externally publishedYes
Event32nd AIAA Fluid Dynamics Conference and Exhibit 2002 - St. Louis, MO, United States
Duration: Jun 24 2002Jun 26 2002

Publication series

Name32nd AIAA Fluid Dynamics Conference and Exhibit

Other

Other32nd AIAA Fluid Dynamics Conference and Exhibit 2002
CountryUnited States
CitySt. Louis, MO
Period6/24/026/26/02

ASJC Scopus subject areas

  • Engineering (miscellaneous)
  • Aerospace Engineering

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