A Study on the Transitional Shock Separation Patterns in an Over-Expanded Nozzle

과팽창 노즐에서 발생하는 충격파 박리 패턴의 천이에 관한 연구

  • 이종성 (안동대학교 대학원 기계공학과) ;
  • ;
  • 김희동 (안동대학교 기계공학과)
  • Received : 2010.03.22
  • Accepted : 2010.05.13
  • Published : 2010.06.30

Abstract

Numerical investigation was carried out on axisymmetric over-expanded rocket nozzle to predict flow fields of transitional shock separation patterns. The unsteady, compressible N-S equations with k-$\omega$ SST for turbulence model closure were solved using a fully implicit finite volume scheme. Computed results were in good agreement with previous experimental works. It was found that strong side-loads were generated during the transition of RSS to FSS due to the development of a vortex ring in the inviscid jet core region. Hysteresis phenomenon exhibited by the shock-separation patterns was also found during the start-up and shut-down processes.

Acknowledgement

Supported by : 한국연구재단

References

  1. Rao, G.V.R., "Exhaust Nozzle Contours for Optimum Thrust," AIAA Journal of Jet Propulsion, Vol. 28, June, 1958, pp.377-383 https://doi.org/10.2514/8.7324
  2. Hoffman, J.D., "Design of Compressed Truncated Perfect Nozzles," AIAA Journal of Propulsion and Power, Vol. 3, No. 2, 1987, pp.150-156 https://doi.org/10.2514/3.22967
  3. Nagdewe, S.P., 이종성, 김희동, "로켓노즐에 서 발생하는 횡력변동에 관한 연구," 한국추진공학회 춘계학술대회 논문집, 2009, pp.315-319
  4. Yonezawa, K., Yamashita, Y., Tsujimoto, Y., Watanabe, Y. and Yokota, K., "Effect of Contour on Flow Separation in Overexpanded Rocket Nozzles," Journal of Fluid Science and Technology, Vol. 2, No. 1, 2007, pp.97-108 https://doi.org/10.1299/jfst.2.97
  5. Nave, L.H. and Coffey, G.A., "Sea Levels Side Loads in High-Area-Ratio Rocket Engines," AIAA Paper 73-1284, 1973
  6. Chen, C. L., Chakravarthy, S. R., and Hung, C. M., "Numerical Investigation of Separated Nozzle Flows," AIAA Journal, Vol. 32, No. 9, 1994, pp.1836-1843 https://doi.org/10.2514/3.12181
  7. Frey, M. and Hagemann, G., "Restricted Shock Separation in Rocket Nozzles," AIAA Journal of Propulsion and Power, Vol. 16, No. 3, 2000, pp.478-484 https://doi.org/10.2514/2.5593
  8. Menter, F. R., "Two-Equation Eddy-Viscosity Turbulence Models for Engineering Applications," AIAA Journal, Vol. 32, No. 8, 1994, pp.1598-1605 https://doi.org/10.2514/3.12149
  9. Thi Nguyen, A. and Deniau, H., Girard, S. and Alziary de Roquefort, T., "Unsteadiness of Flow Separation and End-Effects Regime in a Thrust-Optimized Contour Rocket Nozzle," Flow, Turbulence and Combustion, Vol. 71, 2003, pp.161-181 https://doi.org/10.1023/B:APPL.0000014927.61427.ad
  10. Hadjadj A., Onofri M., "Nozzle Flow Separation," Shock Wave Journal, Vol. 19, No. 3, 2009, pp.163-169 https://doi.org/10.1007/s00193-009-0209-7
  11. Yonezawa, K., Morimoto, T., Tsujimoto, Y., Watanabe, Y. and Yokota, K., "A Study of an Asymmetric Flow in an Overexpanded Rocket Nozzle," Journal of Fluid Science and Technology, Vol. 2, No. 2, 2007, pp.400-409 https://doi.org/10.1299/jfst.2.400
  12. Nebbache, A. and Pilinski, C., "Pulsatory Phenomenon in a Thrust Optimized Contour Nozzle," Aerospace Science and Technology, Vol. 10, 2006, pp.295-308 https://doi.org/10.1016/j.ast.2005.07.002
  13. Nasuti, F. and Onofri, M., "Viscous and Inviscid Vortex Generation During Startup of Rocket Nozzles," AIAA Journal, Vol 36, No. 5, 1998, pp.809-815 https://doi.org/10.2514/2.440