국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Low-speed Wind Tunnel Tests on the Joined-Wing Aircraft Models
저자	Hirotoshi FUJIEDA, Fumiko ITO, Akihito IWASAKI, Toshimi FUJITA, NAOTO TAKIZAWA
Keyword	Joined-wing aircraft; Low-speed wind tunnel tests
URL	http://send.nal.go.jp/send/jpn/dlpdf.php3/naltm00695.pdf?id=NALTM0000695
보고서번호	NAL TM-695
발행년도	1996.7
출처	NAL (National Aerospace Laboratory of Japan)
ABSTRACT	This report describes the aerodynamic characteristics of the joined-wing aircraft obtained by low-speed wind tunnel tests.The joined-wing aircraft consists of a swept-back(40° sweep angle at 25％ chord line)main wing without a dihedral angle(0°)and a swept-forward horizontal tail wing(-25° sweep angle at 25％ chord line)with a hedral angle of -22°.The tests were conducted on fouril span increases and that the configuration in which the leading edge of the horizontal tail tip were joined to the wing with no overlap had better aerodynamic characteristics than the configuration with overlap.The spanwise joint location of horizontal tail significantly influenced the aerodynamic characteristics of the joined-wing aircraft.By improving the leading edge of the wing,the separation of wing tip delayed the attack angle by about 5° and the maximum lift coefficient and lift-to-drag ratio increased.