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research-article

Experimental Investigation on Infrared Signatures of the Subscale Models of Axisymmetric Vectoring Exhaust Nozzle with Film Cooling and Low-emissivity Coating

[+] Author and Article Information
Jian Liu

Nanjing University of Aeronautics and Astronautics, College of Power and Energy Engineering, 29 Yudao Street, Nanjing, Jiangsu Province, 210012, P. R. China
lukeliu1989@163.com

Honghu Ji

Nanjing University of Aeronautics and Astronautics, College of Power and Energy Engineering, 29 Yudao Street, Nanjing, Jiangsu Province, 210012, P. R. China
jhhpe@nuaa.edu.cn

1Corresponding author.

ASME doi:10.1115/1.4038813 History: Received July 31, 2017; Revised November 14, 2017

Abstract

Investigations on infrared radiation suppression of axisymmetric vectoring exhaust nozzle are meaningful, due to the requests for maneuverability and infrared stealth capability of aircrafts. In this paper, the synthetic suppression scheme of film cooling and low-emissivity coating was adopted on the center body and divergent flaps of the nozzles at 0°, 10°, and 20° vectoring angles. The infrared signatures of both the baseline axisymmetric vectoring exhaust nozzles and the nozzles with infrared suppression were measured. Comparing the infrared signatures of the nozzles with and without infrared suppression measures, the infrared suppression effectiveness of the film cooling and low-emissivity coating was obtained. The investigation results indicate that the infrared signatures of axisymmetric vectoring exhaust nozzle decrease with the increase of vectoring angle. The film cooling enables a remarkable decrease of the infrared signatures of axisymmetric vectoring exhaust nozzles. The synthetic suppression of film cooling and low-emissivity coating enables a further decrease of infrared signatures. For the case studied in this paper, the integrated radiation intensities of the nozzles with film cooling and low-emissivity coating at 0°, 10°, and 20° vectoring angles are decreased by 52.3%, 57.9%, and 37.2% at 0° measurement angle, respectively.

Copyright (c) 2017 by ASME
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