Accession Number : AD0642360
Title : SUBSONIC FLOW VISUALIZATION AND AERODYNAMIC FORCE TESTS ON CONES.
Descriptive Note : Master's thesis,
Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
Personal Author(s) : Gamble,Wayne W.
Report Date : JUN 1966
Pagination or Media Count : 76
Abstract : An aluminum cone with an apex angle of 60 degrees was tested. Lift, drag and pitching moment were measured at angles of attack from -5 to 90 degrees and from 90 to 180 degrees at dynamic pressures of 100 lb./sq. ft. and 75 lb./sq. ft., respectively. The fluorescent-oil film method was used for surface flow visualization. Observations of oil-flow patterns, illustrated with photographs, are described for angles of attack from 0 to 180 degrees. The force data was corrected for tare, interference and three-dimensional wind tunnel effects; this was plotted in coefficient form versus angle of attack. Abrupt changes in forces near 72 degrees angle of attack were caused by separation of a complex flow phenomenon on the downwind lateral surface of the cone. The oil flow on the lateral surface of the cone near 90 degrees angle of attack was found to be similar to the oil flow observed on a right circular cylinder. (Author)
Descriptors : (*CONICAL BODIES, *AERODYNAMIC LOADING), (*SUBSONIC FLOW, FLOW VISUALIZATION), LIFT, DRAG, PITCH(MOTION), MOMENTS, ANGLE OF ATTACK, FLUORESCENCE, FILMS, OILS
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE