Flowfield calculation coupled with fuel surface regression in combustion chamber for swirling-oxidizer-type hybrid rocket engine

Takaya Koda, Yousuke Ogino, Keisuke Sawada

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

Abstract

In order to predict local regression rate in swirling-oxidizer-type hybrid rocket chamber, we conduct a loosely coupled computation of flowfield with surface regression of solid fuel in combustion chamber. Three-dimensional Navier-Stokes equations with thermochemical assumption are solved. The local regression rate is determined from considering heat balance on fuel surface. A proper time interval for surface regression in loosely coupled calculation is examined in a test case for simplified chamber model. This method is also applied to solve the flowfield in realistic swirling-oxidizer-type chamber. The computed time-averaged local regression rate along the fuel surface shows a qualitative agreement with the experimental results, whereas the computed regression rate becomes smaller than those for experimental data with similar oxidizer mass flux. Possible causes for this discrepancy are discussed.

Original languageEnglish
Title of host publication51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013
Publication statusPublished - 2013 Aug 19
Event51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013 - Grapevine, TX, United States
Duration: 2013 Jan 72013 Jan 10

Publication series

Name51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013

Other

Other51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013
CountryUnited States
CityGrapevine, TX
Period13/1/713/1/10

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

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    Koda, T., Ogino, Y., & Sawada, K. (2013). Flowfield calculation coupled with fuel surface regression in combustion chamber for swirling-oxidizer-type hybrid rocket engine. In 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013 (51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013).