Prediction of the Rear Fuselage Temperature with Radiation Shield
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.
[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.
[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.
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:63505", author = "Kyung Joo Yi and Seung Wook Baek and Sung Nam Lee and Man Young Kim and Won Cheol Kim and Gun Yung Go", title = "Prediction of the Rear Fuselage Temperature with Radiation Shield", abstract = "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", volume = "5", number = "11", pages = "2507-4", }