국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Effect of Blade Tip Planform on Shock Wave of Advancing Helicopter Blade
저자	Takashi Aoyama, Shigeru SAITO
Keyword	Helicopter Blade; Tip Planform; Shock Wave; Advancing Side
URL	http://send.nal.go.jp/send/jpn/dlpdf.php3/naltr01275.pdf?id=NALTR0001275
보고서번호	NAL TR-1275
발행년도	1995.7
출처	NAL (National Aerospace Laboratory of Japan)
ABSTRACT	od was added to obtain the unsteady solution in forward flight.The calculations were performed for blades having the NACA0012 airfil section along the entire blade span to investigate the planform effect alone.The parametric study clarified the effect of the sweep and the taper on shock wave behavior.In addition,a guideline of the blade planform design for the advancing blade was suggested,and a newlydevised tip planform which prevents shock wave generation was proposed.The effectiveness of the BERP and ONERA PF2 planform which are examples of advenced tip planforms were also presented.