Numerical study on attack angle characteristics of nacelle inlet based on airworthiness standard

Abstract

Abstract: In order to study the effect of flow separation in the nacelle inlet caused by high attack angle of transport aircraft during climbing stage on the intake performance, the nacelle inlet of large bypass ratio turbofan engine DGEN380 is taken as the research object. The flow field at 0 °- 40 ° attack angle is simulated respectively. It is found that the low momentum fluid accumulation and flow separation in the nacelle inlet caused by the increase of attack angle are the main reasons for the total pressure distortion. The results show that with the increase of attack angle, the total pressure recovery coefficient decreases and the inlet distortion index increases. In the range of 28°-40 ° attack angle, the total pressure recovery coefficient and inlet distortion index are more sensitive to the changes of angle of attack(AOA) and Mach number due to different intensity of separation of air flow in the nacelle inlet. In this range, at the same attack angle, the greater the Mach number, the easier the separation of flow.

Key words: font-size:15.04px, ">nacelle inlet, attack angle characteristics, inlet distortion, airworthiness standard, numerical simulation

CLC Number:

V231.3

BAI Jie, GUO Chongjia , FU Wenguang , SUN Peng . Numerical study on attack angle characteristics of nacelle inlet based on airworthiness standard[J]. Journal of Civil Aviation University of China, 2023, 41(1): 1-6.

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