Commenced in January 2007
Frequency: Monthly
Edition: International
Paper Count: 31743
Prediction of the Rear Fuselage Temperature with Radiation Shield

Authors: Kyung Joo Yi, Seung Wook Baek, Sung Nam Lee, Man Young Kim, Won Cheol Kim, Gun Yung Go


In order to enhance the aircraft survivability, the infrared signatures emitted by hot engine parts should be determined exactly. 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 characteristics of an aircraft nozzle is performed and its temperature distribution along each component wall is predicted. The radiation shield is expected to reduce the skin temperature of rear fuselage. The effect of material characteristic of radiation shield on the heat transfer is also investigated. Through this numerical analysis, design parameters related to the susceptibility of aircraft are examined.

Keywords: Infrared signature, Nozzle flow, Radiation shield, Rear fuselage temperature, Susceptibility

Digital Object Identifier (DOI):

Procedia APA BibTeX Chicago EndNote Harvard JSON MLA RIS XML ISO 690 PDF Downloads 1948


[1] 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.
[2] 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.
[3] Hunter, C. A., "Experimental Investigation of Separated Nozzle Flows", Journal of Propulsion and Power, Vol. 20, No. 3, 2004, pp. 527-532.
[4] 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.
[5] 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.
[6] Liou, M. S., "A Sequel to AUSM: AUSM+-up for All Speeds", Journal of Computational Physics, Vol. 214, 2006, pp. 137-170.
[7] Yi, K .J., Baek, S. W., Lee, S. N., Kim, M. Y., and Kim, W. C., "Effects of Nozzle Characteristics on the Rear Fuselage Temperature Distribution (Periodical styleÔÇöSubmitted for publication)," Journal of the KSAS, submitted for publication.