국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	BOUNDARY-LAYER TRANSITION RESULTS FROM THE F-16XL-2 SUPERSONIC LAMINAR FLOW CONTROL EXPERIMENT
저자	Laurie A. Marshall
Keyword	F-16XL; Hot film; Laminar flow control; Suction; Transition
URL	http://www.dfrc.nasa.gov/DTRS/1999/PDF/H-2382.pdf
보고서번호	NASA-TM-1999-209013
발행년도	1999
출처	NASA Dryden Flight Research Center
ABSTRACT	A variable-porosity suction glove has been flown on the F-16XL-2 aircraft to demonstrate the feasibility of this technology for the proposed High-Speed Civil Transport (HSCT). Boundary-layer transition data have been obtained on the titanium glove primarily at Mach 2.0 and altitudes of 53,000?5,000 ft. The objectives of this supersonic laminar flow control flight experiment have been to achieve 50- to 60-percent뻙hord laminar flow on a highly swept wing at supersonic speeds and to provide data to validate codes and suction design. The most successful laminar flow results have not been obtained at the glove design point (Mach 1.9 at an altitude of 50,000 ft). At Mach 2.0 and an altitude of 53,000 ft, which corresponds to a Reynolds number of 22.7 x 10 to the sixth power, optimum suction levels have allowed long runs of a minimum of 46-percent뻙hord laminar flow to be achieved. This paper discusses research variables that directly impact the ability to obtain laminar flow and techniques to correct for these variables.