한국전산유체공학회:학술대회논문집
- 2011.05a
- /
- Pages.465-468
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- 2011
COMPUTATIONAL PREDICTION OF ICE ACCRETION AROUND AIR INTAKE OF AIRCRAFT
CFD를 이용한 항공기 공기 흡입구 주위 결빙 예측
- Jung, K.Y. ;
- Ahn, G.B. ;
- Jung, S.K. ;
-
Myong, R.S.
;
- Cho, T.H. ;
- Shin, H.B. ;
-
Jung, J.H.
;
- Choi, Y.H. ;
- Kim, J.H.
- 정기영 (경상대학교 항공특성화대학원) ;
- 안국빈 (경상대학교 항공특성화대학원) ;
- 정성기 (경상대학교 항공특성화대학원) ;
-
명노신
(경상대학교 항공특성화대학원 및 항공기부품기술연구소)
;
- 조태환 (경상대학교 항공특성화대학원 및 항공기부품기술연구소) ;
- 신훈범 (한국항공우주산업) ;
-
정주현
(한국항공우주산업)
;
- 최영호 (국방과학연구소) ;
- 김정훈 (국방기술품질원)
- Published : 2011.05.26
Abstract
Ice accretion on aircraft surface can greatly deteriorate the safety of aircraft. In particular, it can be a cause of impediment for aircraft performances such as aerodynamic characteristics, control, and engine. Numerical simulation of icing accretion based on the state-of-art CFD techniques can be alternative to expensive icing wind tunnel test or flight test. In this study, icing conditions are defined in order to predict the ice accretions around the air intake of aircraft. Then the range and amount of ice accretion on the intake in icing wind tunnel were investigated In addition, a study on the size effect of icing wind tunnel was conducted in order to check the compatibility with the real in-flight test environment.