국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	IN-FLIGHT TRANSITION MEASUREMENT ON A 10 DEG CONE AT MACH NUMBERS FROM 0.5 TO 2.0
저자	D. F. Fisher and N. S. Dougherty, Jr.
Keyword	Boundary layer transition; F-15 aircraft; Flow measurement; In-flight monitoring; Mach number.
URL	http://www.dfrc.nasa.gov/DTRS/1982/PDF/H-1117.pdf
보고서번호	NASA-TP-1971
발행년도	1982
출처	NASA Dryden Flight Research Center
ABSTRACT	Boundary layer transition measurements were made in flight on a 10 deg transition cone tested previously in 23 wind tunnels. The cone was mounted on the nose of an F-15 aircraft and flown at Mach numbers room 0.5 to 2.0 and altitudes from 1500 meters (5000 feet) to 15,000 meters (50,000 feet), overlapping the Mach number/Reynolds number envelope of the wind tunnel tests. Transition was detected using a traversing pitot probe in contact with the surface. Data were obtained near zero cone incidence and adiabatic wall temperature. Transition Reynolds number was found to be a function of Mach number and of the ratio of wall temperature to adiabatic all temperature. Microphones mounted flush with the cone surface measured free-stream disturbances imposed on the laminar boundary layer and identified Tollmien-Schlichting waves as the probable cause of transition. Transition Reynolds number also correlated with the disturbance levels as measured by the cone surface microphones under a laminar boundary layer as well as the free-stream impact.