국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	Aerodynamic Heating Measurements on Hypersonic Flight Experiment（HYFLEX）Vehicle
저자	Keisuke Fujii, Shigeya Watanabe, Masao Shirouzu, Yasutoshi Inoue, Takuji Kurotaki, Tadao Koyama, Syouichi Tsuda, Noriaki Hirabayashi
Keyword	Wind Tunnel Test System; Turbine Powered Simulator; Piping Interference System; Air Bearing
URL	http://send.nal.go.jp/send/jpn/dlpdf.php3/naltr0001415.pdf?id=NALTR0001415
보고서번호	NAL TR-1415
발행년도	2000.12
출처	NAL (National Aerospace Laboratory of Japan)
ABSTRACT	Aerodynamic heating on the Hypersonic Flight Experiment vehicle was measured using newly developed sensors, calibrated by lamp heating tests. These sensors were shown to be of use for flight measurement purposes. The results of the aerodynamic heating measurements on the vehicle were compared with predictions based on cold hypersonicwind tunnel tests and CFD calculations. The flight results on the nose cap were lower than the predictions based on the wind tunnel tests in the stagnation region of aroundt ＝100sec. Comparison with real gas CFD results assuming a fully catalytic wall and non-catalytic wall indicate that this discrepancy is due to the effect of dissociation of the air, and can be explained by the dependence of catalycity on surface temperature.For the measurements on the elevon, an increase in aerodynamic heating caused byboundary layer transition was observed immediately prior to it being observed on thewindward fuselage. Flight data on the windward side of the afterbody show boundarylayer transition and following laminarization, which may be explained qualitatively bythe transition criteria for the attachment line of the yawed cylinder, taking into acc-ount the effect of nose bluntness.