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Journal of the Korea Institute of Military Science and Technology 2002;5(2):83-90.
Effects of LEX on the Vortex Field over a Delta Wing
,
LEX가 델타형 날개의 와류 유동장에 미치는 영향
백승욱, 손명환
공군사관학교 항공우주공학과
Abstract
An experimental study was conducted to investigate the effects of a leading edge extension(LEX) on the vortex flow field over a delta wing by measuring the total pressure distribution in a subsonic wind tunnel. Freestream velocity was 40m/sec and Reynolds number per meter was $1.76{ imes}10^6$. The wing with the LEX experienced a strong interaction between the LEX and wing vortices. As the angle of attack increased, the coupled vortex field of these two vortices maintained its strength and concentricity much better than the vortex field over the wing without the LEX.
Key Words: Leading edge extension, Vortex, Suction pressure
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