국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	SUMMARY OF TRANSITION RESULTS FROM THE F-16XL-2 SUPERSONIC LAMINAR FLOW CONTROL EXPERIMENT
저자	Laurie A. Marshall
Keyword	F-16XL; Hot-films; Laminar flow control; Suction; Transition.
URL	http://www.dfrc.nasa.gov/DTRS/2000/PDF/H-2410.pdf
보고서번호	H-2410
발행년도	2000
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. Boundary-layer transition data on the titanium glove primarily have been obtained at speeds of Mach 2.0 and altitudes of 15,240?6,764 m (50,000?5,000 ft). The objectives of this flight experiment have been to achieve 0.50?.60 chord 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, a speed of Mach 1.9 at an altitude of 15,240 m (50,000 ft); but rather at a speed of Mach 2.0 and an altitude of 16,154 m (53,000 ft). Laminar flow has been obtained to more than 0.46 wing chord at a Reynolds number of 22.7 X 10 to the sixth. A turbulence diverter has been used to initially obtain a laminar boundary layer at the attachment line. A lower-surface shock fence was required to block an inlet shock from the wing leading edge. This paper discusses research variables that directly impact the ability to obtain laminar flow and techniques to correct for these variables.