적외선 신호 분석을 위한 고속 항공기의 공력가열에 관한 효율적 예측

국문 초록 (Abstract)

고속으로 비행하는 항공기의 구성품에 관한 적절한 설계를 위해서는 공기역학적 가열과 표면 온도를 계산하는 능력이 필수적이다. 본 연구에서는 항공기의 공력가열을 효율적으로 계산하기 위한 다양한 경험식들을 분석한 다음, 경험식에 기초한 전산코드를 개발하였다. 계산된 결과는 Navier-Stokes-Fourier 방정식 기반의 ANSYS FLUENT와 경험식에 기초한 ThermoAnalytics사의 MUSES코드의 결과와 비교하였다. FLUENT의 계산결과와는 벽면 및 정체점 온도에 대해 매우 일치하였다. MUSES 코드와도 온도와 열유속에서 각각 1%, 5%의 차이를 보여주어 매우 근접한 결과를 보여 주었다.

다국어 초록 (Multilingual Abstract)

The ability to calculate aerodynamic heating and surface temperature is essential to ensure proper design of aircraft components in high speed flight. In this study, various empirical formulas for efficiently calculating aerodynamic heating of aircraft were first analyzed. A simple computational code based on empirical formulas was developed and then compared with commercial codes; ANSYS FLUENT based on the Navier-Stokes-Fourier equation, and ThermoAnalytics MUSES based on an empirical formula. The code was found to agree well with the results of FLUENT in the wall and stagnation point temperatures. It also showed excellent agreement with MUSES, within 1% and 5% in temperature and heat flux, respectively.

목차 (Table of Contents)

• ABSTRACT
• 초록
• Ⅰ. 서론
• Ⅱ. 비행체 공력가열 모델
• Ⅲ. 공력가열 모델 검증 및 결과
• Ⅳ. 결론
• References

참고문헌 (Reference)

1 차종현, "비행마하수와 형상에 따른 초음속 항공기 표면온도 변화" 한국군사과학기술학회 17 (17): 463-470, 2014

2 박정민, "대한민국에서 운용될 전투기의 환경시험 테일러링 기법 연구" 한국항공우주학회 47 (47): 344-357, 2019

3 Fay, J. A., "Theory of Stagnation Point Heat Transfer in Dissociated Air" 25 (25): 73-85, 1958

4 Ball, R. E., "The Fundamentals of Aircraft Combat Survivability Analysis and Design, AIAA Education Series" AIAA 2003

5 Brown, W. B., "Tables of Exact Laminar Boundary Layer Solutions When the Wall is Porous and Fluid Properties Are Variable" 1951

6 Reed, R. D., "Skin and Structural Temperatures Measured on the X-15 Airplane During a Flight to a Mach Number of 3.3"

7 Desai, S. S., "Relative Roles of Computational Fluid Dynamics and Wind Tunnel Testing in the Development of Aircraft" 84 (84): 49-64, 2003

8 "RadThermIR: Thermal and Infrared Simulation Software" Thermo Analytics Inc 2006

9 Goulard, R., "On Catalytic Recombina - tion Rates in Hypersonic Stagnation Heat Transfer" 28 (28): 737-745, 1958

10 Rao, G. A., "New Criterion for Aircraft Susceptibility to Infrared Guided Missiles" 9 (9): 701-712, 2005

11 Squire, H. B., "Modern Developments in Fluid Dynamics" Oxford University Press 1938

12 Jones, I. P. Jr., "Measurements of Aero- dynamic Heating Obtained During Demonstration Flight Tests of the Douglas D-558-II Airplane" NACA 1952

13 Crocco, L., "Lo Strato Limite Laminare nei Gas" 187 : 1946

14 Lees, L., "Laminar Heat Transfer over Blunt-Nosed Bodies at Hypersonic Flight Speeds" 26 (26): 259-269, 1956

15 김성룡, "KSR-III 공력가열 해석 및 비행시험" 한국항공우주학회 32 (32): 54-63, 2004

16 Kalikhman, L. E., "Heat Transmission in the Boundary Layer" NACA 1949

17 Beckwith, I. E., "Heat Transfer and Recovery Temperatures on a Sphere with Laminar, Transitional, and Turbulent Boundary Layers at Mach Numbers of 2.00 and 4.15" NASA 1957

18 Sibulkin, M., "Heat Transfer Near the Forward Stagnation Point of a Body Revolution" 9 : 570-571, 1952

19 "FLUENT Theory Guide"

20 "FLUENT Basic v13.0"

21 Fleeman, E. L., "Encyclopedia of Aerospace Engineering" 2010

22 Homann, F. Z., "Effect of High Speed Over Cylinder and Sphere" 16 (16): 153-164, 1936

23 van Driest, E. R., "Convective Heat Transfer in Gases" 5 : 339-427, 1959

24 White, J. R., "Aircraft Infrared Principles, Signatures, Threats, and Countermeasures" Naval Air Warfare Center Weapons Division 2012

25 Oh, B. S., "Aerodynamic Heating Analysis of KSR-Ⅱ" 27 (27): 121-127, 1999

26 Moore, L. L., "A Solution of the Laminar Boundary-Layer Equations for a Compressible Fluid with Variable Properties, Including Dissoci-ation" 19 (19): 505-518, 1952