국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Experimental and Numerical Validation of the Natural Laminar Flow Wing of Non-powered Experimental Airplane for Supersonic Transport
저자	SUGIURA Hiroki, TAKAGI Shohei, TOKUGAWA Naoko, NISHIZAWA Akira, YOSHIDA Kenji, NOGUCHI Masayoshi, UEDA Yoshine
Keyword	Transition Measurement; Hot-film; Infrared Camera; Natural Laminar Flow
URL	http://send.nal.go.jp/send/jpn/dlpdf.php3/naltr0001437.pdf?id=NALTR0001437
보고서번호	NAL-TR-1437
발행년도	2002.2
출처	NAL (National Aerospace Laboratory of Japan)
ABSTRACT	Transition characteristics on the natural laminar flow wing of a non-powered scaled supersonic experimental airplane was measured by hot-film sensors and an infrared camera in two supersonic wind tunnels at Mach 2. In order to suppress the growth of crossflow instability which dominates the transition on highly swept wings, the pressure falls very rapidly in the vicinity of leading edge of the wing, so as to minimize the crossflow velocity components. From test results, the unit Reynolds number had no effect on the transition Reynolds numbers of the wing. The transition Reynolds number was 0.8 million at 70% semi-spanwise location at Mach2 at the angle of attack of 2 degrees. Tollmien-Schlichting instability dominates the transition and crossflow instability was found to be suppressed on the wing. Considering the influence of surface roughness and freestream turbulence, the transition at 70% semi-spanwise position at Mach2 at the angle of attack of 2 degrees in flight is estimated to be located at 50% chordwise position.