Journal of the Korea Institute of Military Science and Technology (한국군사과학기술학회지)

The Korea Institute of Military Science and Technology (한국군사과학기술학회)
권호 표지
DOI QR코드

DOI QR Code

Development of Equilibium Flow Calculation Program Using a Modified Newtonian Method

수정 뉴토니안 방법을 이용한 평형유동 해석 프로그램 개발

  • Choi, Jaehyeok (The 1st Research and Development Institute, Agency for Defense Development)
  • 최재혁 (국방과학연구소 제1기술연구본부)
  • Received : 2015.12.23
  • Accepted : 2016.07.08
  • Published : 2016.08.05
Download PDF
⟨ Previous Next ⟩

Abstract

A simple aerodynamic calculation program for high Mach number flow is developed by combining the modified Newtonian method with Tannehill's curve fits for the thermodynamic properties of air in equilibrium state. Aerodynamic characteristics for a parabolic nose are predicted and compared with CFD(Computational Fluid Dynamics) analysis results. Comparison shows good agreements, and the developed program is expected to be a practical tool for slender body aerodynamic calculation for high Mach number flow.

Keywords

References

  1. Frank G. Moore, et al., "Second-Order Shock-Xpansion Theory Extended to Include Real Gas Effects," Naval Surface Warfare Center, Navswc TR90-683, 1992.
  2. John D. Anderson, "Modern Compressible Flow with Historical Perspective 3rd Edition," McGrawHill, 1221 Avenue of the Americas, New York, 2003.
  3. John D. Anderson, "Hypersonic and High-Temperature Gas Dynamics Second Edition," AIAA, 1801 Alexander Bell Drive, Reston, Virginia 20191-4344, 2006.
  4. J. C. Tannehill, et al., "Simplified Curve Fits for the Thermodynamic Properties of Equilibrium Air," NASA, NASA Reference Publication 1181, 1987.
  5. Hayes, J. R. and Neumann, R. D., "Introduction to the Aerodynamic Heating Analysis of Supersonic Missile," Tactical Missile Aerodynamics: Prediction Methodology, Progress in Astronautics and Aeronautics, AIAA, Vol. 142, pp. 63-114, 1991.
  6. Truitt, R. W., Fundamentals of Aerodynamic Heating, The Ronald Press Company, New York, 1960, Shock Wave Parameters in Equilibrium Air, Cornell AeroLab.Report CAL-III, 1961.
  7. S. Y, Jung, S. J, Yoom, W. S., Byon, C. S., Ann, "Aerodynamic Heating Analysis of Spike-Nosed Missile," Journal of the Korea Institute of Military Science and Technology, Vol. 7, No. 3, 2004.
  8. Wilbur L. Hankey, "Re-Entry Aerodynamics," AIAA Education Series, American Institute of Aeronautics and Astronautics Inc., 1988.
  9. William A. Wood., "Hypersonic Pitching-Moment Shift for Stardust Reentry Capsule Forebody," NASA NASA/TM-97-206266, 1997.
  10. PRICOP, Mihai Victor, ANDREI, Irina Carmen, BOSCOIANU, Mircea, "Application of Modified Newton Flow Model to Earth Reentry Capsules," INCAS Bulletin, 2014 Special Issue, Vol. 6, Issue 1, pp. 129-134, 2014.
  11. George S. Dulikravich, RN Buss, EJ Strang, S Lee, "Aerodynamic Shape Optimization of Hypersonic Missile," AIAA Paper, 1990.
  12. George S. Dulikravich, SG Sheffer, "Aerodynamic Shape Optimization of Arbitrary Hypersonic Vehicles," Proc. of 3rd International Conference on Inverse Design Concepts and Optimization in Engineering Sciences, 1991.
  13. Michael J. Grant and Robert D. Braun, "Analytic Hypersonic Aerodynamics for Conceptual Design of Entry Vehicles," 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, 2010.
  14. M. K. Kim, "Aerodynamic Analysis Software based on Newtonian Mtehod," ADDS-2014-0214, Agency for Defense Development, 2014.
  15. S. Y., Jung, O. H. Noh, and W. S., Byon, "Numerical Analysis of Thermal/Chemical Non- Equilibrium Flow Over a Blunt Body," The Korean Society for Aeronautical and Space Sciences, 1995.
  16. Wittliff, Charles E., and Curtis, James T., "Normal Shock Wave Parameters in Equilibrium Air," Cornell AeroLab.Report CAL-III, 1961.