한국항공우주학회지 (Journal of the Korean Society for Aeronautical & Space Sciences)

  • 제46권8호
  • /
  • Pages.652-661
  • /
  • 2018
  • /
  • 1225-1348(pISSN)
  • /
  • 2287-6871(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
권호 표지
DOI QR코드

DOI QR Code

충격파 풍동의 극초음속 노즐 설계를 위한 Quasi 1D 비평형 해석 및 검증

Quasi 1D Nonequilibrium Analysis and Validation for Hypersonic Nozzle Design of Shock Tunnel

  • Kim, Seihwan (Daewoo Shipbuilding & Marine Engineering Co., Ltd.) ;
  • Lee, Hyoung Jin (Inha University, Department of Aerospace Engineering)
  • 투고 : 2018.02.07
  • 심사 : 2018.07.27
  • 발행 : 2018.08.01
PDF 다운로드
⟨ 이전 논문 다음 논문 ⟩

초록

고속 고온 유동에서 나타나는 고온 기체 현상을 모사하기 위해서는 마하수뿐 아니라 절대속도도 재현할 수 있어야 한다. 이러한 유동을 초음속 유동과 구분하여 극고속 유동이라 부르며, 충격파 터널과 같은 고엔탈피 시험 장치를 통해 연구가 이루어지고 있다. 그러나 이러한 고엔탈피 시험 장비는 높은 온도와 압력 때문에 노즐에서 열화학적 비평형 현상을 경험하게 되며 기존의 이론적 방법으로 그 실험 조건을 규정하기 어렵다. 이에 본 연구에서는 알려진 비평형 노즐 코드의 단점들을 보완하고 충격파 터널의 운용 조건에서 시험부 유동 특성을 빠르게 예측하기 위하여 열화학적 비평형을 고려한 준 1차원 노즐 해석 코드를 개발하였다. 개발된 코드는 시험 결과 및 2차원 축대칭 해석 결과와 비교를 통하여 충격파 풍동 시험부 유동 조건 예측을 위한 활용성 및 한계를 살펴보았다.

It is necessary to resolve the absolute velocity as well as Mach number to reflect the high temperature effect in high speed flow. So this region is classified as high enthalpy flows distinguished from high speed flows. Many facilities, such as arc-jet, shock tunnel, etc. has been used to obtain the high enthalpy flows at the ground level. However, it is difficult to define the exact test condition in this type of facilities, because some chemical reactions and energy transfer take place during the experiments. In the present study, a quasi 1D code considering the thermochemical non-equilibrium effect is developed to effectively estimate the test condition of a shock tunnel. Results show that the code gives reasonable solution compared with the results from the known experiments and 2D axisymmetric simulations.

키워드

참고문헌

  1. Park, C., Nonequilibrium Hypersonic Aerothermodynamics, A Willey-Interscience Publication, 1990.
  2. Bray, K. N. C., "Atomic Recombination in a Hypersonic Wind Tunnel Nozzle," Journal of Fluid Mechanics, Vol. 6, No. 1, 1959, pp.1-32 https://doi.org/10.1017/S0022112059000477
  3. Anderson, J. D., "A Time-Dependent Analysis For Quasi-One-Dimensional Nozzle Flows with Vibrational and Chemical Nonequilibrium," Technical Report, NOLTR, 1969. pp.69-52
  4. Park, C., and Lee, S.H., "Validation of Multitemperature Nozzle Flow Code," Journal of Thermophysics and Heat Transfer, Vol. 9(1), 1995, pp. 9-16 https://doi.org/10.2514/3.622
  5. MacLean, M., Holden, M., Wadhams, T. and Parker, R., "A Computational Analysis of Therochemical Studies in the LENS facilities," AIAA 2007-121, 2007
  6. Karl, S., Schramm, J. M., and Hannemann, K., "High Enthalpy Cylinder Flow in HEG: A Basis for CFD Validation," AIAA 2003-4252, 2003
  7. Dunn, M. G., and Kang, S. W., "Theoretical and Experimental Studies of Reentry Plasma," NASS CR-2232, 1973
  8. Candler, G. V., and MacCormach, R. W., "Computation of Weakly Ionized Hypersonic Flows in Thermochemical Nonequilibrium," Journal of Thermophysics and Heat Transfer, Vol. 5, No. 3, 1991, pp.266-273 https://doi.org/10.2514/3.260
  9. Lobb, K., "Experimental Measurement of Shock Detachment Distance on Sphere Fired in Air at Hypervelocities," The High Temperature Aspect of Hypersonic Flow, W.C. Nelson(ed) Pergamon Press, 1964, pp.519-527
  10. Na, J. J., Lee, J. M., Kwon, M. C., and Hwang, K. Y., "Analysis on the Nonequilibrium Arc-Jet Flow," Proceeding of The Korean Society for propulsion Engineering Spring Conference, 2013, pp.234-239.
  11. Na, J. J., "Determination of Stagnation Point Parameters in the Non-equilibrium Shock Flow," Proceeding of The Korean Society for Aeronautical and Space Sciences Spring Conference, 2011, pp.65-69.
  12. Lee, S. H., Park, G. S., and Kim J. G., "Non-Equilibrium Flow Analysis of a Shock Tunnel," KSCFE Conference, 2017, pp. 24-25.
  13. C. F. H., "Approximations for the Thermodynamic and Transport Properties of High-Temperature Air," NACA, Technical Note 4150, 1958.
  14. Park, C., "Assessment of two-temperature kinetic model for ionizing air," Journal of Thermophysics, Vol. 3, No. 3, 1989, pp.233-244 https://doi.org/10.2514/3.28771
  15. Millikan, R. C., and White, D. R., "Systematics of vibrational relaxation," Journal of Chemical Physics, Vol. 39, No. 12, 1963, pp.3209-3213 https://doi.org/10.1063/1.1734182
  16. Park, C., "Thermo chemical relaxation in Shock Tunnels," Journal of Thermophysics and Heat Transfer, Vol. 20, No. 5, 2006, pp.689-698. https://doi.org/10.2514/1.22719
  17. Park, C., "Review of Chemical-Kinetic Problems of Future NASA Mission, I:Earth Entries," Journal of Thermophysics and Heat Transfer, Vol. 7, No. 3, 1993, pp.385-398. https://doi.org/10.2514/3.431
  18. Goodwin, D., "CANTERA Object-Oriented Software for Reaction & Flows," 1st CANTERA Workshop, 2004.
  19. McIntosh, M. K., Computer program for the numerical calculation of frozen and equilibrium conditions in shock tunnels., Technical Report, Australian National University, Canberra, 1968.
  20. MacDermott, W. N., and Dix, R. E., "Mass Spectrometric Analysis of Nonequilibrium Air," AIAA Journal, Vol. 10, No. 4, 1972, pp. 494-499. https://doi.org/10.2514/3.50125