국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	THERMAL ANALYSIS OF A METALLIC WING GLOVE FOR A MACH-8 BOUNDARY-LAYER EXPERIMENT
저자	Leslie Gong and W. Lance Richards
Keyword	Aerodynamic heating; Boundary layer transition; Finite element modeling; Hypersonics; Pegasus ? Thermal analysis
URL	http://www.dfrc.nasa.gov/DTRS/1998/PDF/H-2259.pdf
보고서번호	NASA-TM-1998-206555
발행년도	1998
출처	NASA Dryden Flight Research Center
ABSTRACT	A metallic ?love?structure has been built and attached to the wing of the Pegasus ?space booster. An experiment on the upper surface of the glove has been designed to help validate boundary-layer stability codes in a free-flight environment. Three-dimensional thermal analyses have been performed to ensure that the glove structure design would be within allowable temperature limits in the experiment test section of the upper skin of the glove. Temperature results obtained from the design-case analysis show a peak temperature at the leading edge of 490 좫. For the upper surface of the glove, approximately 3?n. back from the leading edge, temperature calculations indicate transition occurs at approximately 45 sec into the flight profile. A worst-case heating analysis has also been performed to ensure that the glove structure would not have any detrimental effects on the primary objective of the Pegasus ?launch. A peak temperature of 805 좫 has been calculated on the leading edge of the glove structure. The temperatures predicted from the design case are well within the temperature limits of the glove structure, and the worst-case heating analysis temperature results are acceptable for the mission objectives.