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http://dx.doi.org/10.5139/JKSAS.2011.39.12.1141

Effects of Nozzle Characteristics on the Rear Fuselage Temperature Distribution  

Yi, Kyung-Joo (KAIST 항공우주공학과)
Baek, Seung-Wook (KAIST 항공우주공학과)
Lee, Sung-Nam (한국원자력연구원)
Kim, Man-Young (전북대학교 항공우주공학과)
Kim, Won-Cheol (국방과학연구소)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.39, no.12, 2011 , pp. 1141-1149 More about this Journal
Abstract
In order to enhance the aircraft survivability, infrared signatures emitted by engine parts should be diminished. For its reduction it is necessary for the rear fuselage temperature to be decreased. In this study, numerical modeling of flow fields and heat transfer of nozzle is performed and its temperature distribution along each component wall is predicted. The effects of material characteristics and shape of nozzle wall and radiation shield on the heat transfer are also investigated. Through this numerical analysis, design parameters related to the susceptibility of aircraft are examined.
Keywords
Susceptibility; Infrared Signature; Nozzle Flow; Rear Fuselage Temperature;
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  • Reference
1 Mehta, R. C. and Jayachandran, T., "A Fast Algorithm to Solve Viscous Two-Phase Flow in an Axisymmetric Rocket Nozzle," International Journal for Numerical Methods in Fluids, Vol. 26, 1998, pp.501-517.   DOI
2 Cuffel, R. F., Back, L. H., and Massier, P. F., "Transonic Flowfield in a Supersonic Nozzle with Small Throat Radius of Curvature," AIAA Journal, Vol. 7, No. 7, 1969, pp.1364-1366.   DOI
3 Mahulikar, S. P., Kolhe, P. S., and Rao, G. A., "Skin-Temperature Prediction of Aircraft Rear Fuselage with Multimode Thermal Model," Journal of Thermophysics and Heat Transfer, Vol. 19, No. 1, 2005, pp.114-124.   DOI   ScienceOn
4 Mahulikar, S. P., Sonawane, H. R., and Rao, G. A., "Infrared Signature Studies of Aerospace Vehicles," Progress in Aerospace Sciences, Vol. 43, 2007, pp.218-245.   DOI   ScienceOn
5 Shan, Y. and Zhang, J. -Z., "Numerical Investigation of Flow Mixture Enhancement and Infrared Radiation Shield by Lobed Forced Mixer," Applied Thermal Engineering, Vol. 29, 2009, pp.3687-3695.   DOI   ScienceOn
6 임상민, 김병로, "IR 방사 수준 변화에 따른 항공기 생존성 및 치사성 변화 연구," 한국항공우주학회 2008년도 춘계학술발표회 논문집, 2008, pp.855-858.
7 Hosseini, R., Rahimian, M. H., and Mirzaei, M., "Performance of Two Different High-Accuracy Upwind Schemes in Inviscid Compressible Flow Fields," Journal of Computational Fluids Engineering, Vol. 10, No. 1, 2005, pp.99-106.
8 Hunter, C. A., "Experimental Investigation of Separated Nozzle Flows", Journal of Propulsion and Power, Vol. 20, No. 3, 2004,pp.527-532.   DOI   ScienceOn
9 Weiss, J. M. and Smith, W. A., "Preconditioning Applied to Variable and Constant Density Flows," AIAA Journal, Vol. 33, No. 11, 1995, pp.2050-2057.   DOI   ScienceOn
10 Liou, M. S., "A Sequel to AUSM: AUSM+-up for All Speeds", Journal of Computational Physics, Vol. 214, 2006, pp.137-170.   DOI   ScienceOn
11 Hellsten, A. and Laine, S., "Extension of k-$\omega$-SST Turbulence Models for Flows over Rough Surfaces," AIAA Paper 97-3577, 1997.
12 Chai, J. C., A Finite-Volume Method for Radiation Heat Transfer, Ph. D. Thesis, University of Minnesota, Minneapolis, MN, 1994.
13 김만영, 열복사를 고려한 3차원 연소기 내의 연소 특성, 박사학위논문, 한국과학기술원, 대전, 1999.