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

  • 제11권4호
  • /
  • Pages.20-28
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  • 2008
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  • 1598-9127(pISSN)
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  • 2636-0640(eISSN)
한국군사과학기술학회 (The Korea Institute of Military Science and Technology)
권호 표지

초음속 유도탄 동체와 날개의 공력가열 해석

Aerodynamic Heating Analysis of Supersonic Missile Body and Fin

  • 발행 : 2008.08.30
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초록

Missile operating at supersonic conditions experiences considerable high temperature environments that is caused by aerodynamic heating as a result of the temperature gradient through boundary layer that surrounds it. This is one of important problems to the designer due to temperature limitation of structural materials. Because prediction of aerodynamic heating on missile needs unsteady calculation according to a flight trajectory, approximate method approach is efficient at design stage. In this paper, improved aerodynamic heating analysis scheme is introduced, which calculates heat flow and temperature by simple pressure field prediction on a missile body and fin. The prediction results are compared with measured data and MINIVER codes results.

키워드

참고문헌

  1. Hender, D. R., Gunkel, R. J., 'A Miniature Version of The JA70 Aerodynamic Heating Computer Program, H800(MINIVER)', McDonnel Douglas, June 1970
  2. Engel, C. D., 'Miniver Upgrade for the AVID System, Vol. 1 : Lanmin User's Manual', NASA Contractor Report 172212, 1983
  3. DiCristina, V., 'Three-Dimensional Laminar Boundary Layer Transition on a Sharp 8o Cone at Mach 10', AIAA Journal, Vol. 8, No. 5, pp. 852-856, 1970 https://doi.org/10.2514/3.5777
  4. Syvertson, C. A. and Dennis, D. H., 'A Second-Order Shock Expansion Method Applicable to Bodies of Revolution Near Zero Lift', NACA Report 1328, 1957
  5. Jackson, C. M., Jr., Sawyer, W. C. and Smith, R. S., 'A Method for Determining Surface Pressure on Blunt Bodies of Revolution at Small Angles of Attack in Supersonic Flow', NASA TN D-4865, 1968
  6. DeJarnette, F. R. and Ford, C. P., 'Calculation of Pressure on Bodies at Low Angles of Attack in Supersonic Flow', J. of Spacecraft, Vol. 17, No. 6, Nov-Dec. 1980
  7. Thompson, M. J., 'A Note on the Calculation of Oblique Shock Wave Characteristics', J. of the Aeronautical Science, Nov. 1950
  8. Eckert, E. R. G., 'Survey of Boundary Heat Transfer at High Velocity and High Temperature', WADC, Tech Report 59-624, Apr. 1960
  9. Morgan, V. T., ' The Overall Convective Heat Transfer from Smooth Circular Cylinder", in T. F. Irvine and J. P. Hartnett, Eds., Advances in Heat Transfer, Vol. 11, Academic Press, New York, pp. 199-264, 1975
  10. Anderson, D. A., Tannehill, J. C. and Pletcher, R. H., 'Computational Fluid Mechanics and Heat Transfer', McGraw-Hill Book Company, 1984
  11. 선철, 안창수, '초음속 유도탄 공력가열 예측', 한국전산유체공학회 춘계학술대회, 2007