국내 최대 기계 및 로봇 연구정보

공학설계D/B

공학설계D/B 게시판 내용
Volume Title	Aerodynamics
Volume No	AEROFOILS AND WINGS - Aerofoils at supersonic speeds. Critical Mach number and pressure coefficient. Flat plates.
DATA Title	Profile drag coefficients for two-dimensional biconvex aerofoil with zero heat transfer at supersonic speeds.
DATA Item	Aero W.S.02.04.13
KEYWORD	aerofoil, biconvex, drag, flow, profile, supersonic, airfoil, convex, double
ISBN
ABSTRACT	ESDU Aero W.S.02.04.13 gives curves of profile drag of biconvex aerofoils plotted against transition position as a fraction of chord for values of freestream Mach number of 1.5, 2.5 and 5, thickness chord ratios of 0.05 and 0.1 and three Reynolds numbers. It is recommended that the curves of ESDU Aero W.S.02.04.12, which apply for a thickness chord ratio of zero, be used to guide extrapolation to thickness chord ratios below 0.05 as shown in the worked example of the use of the curves. The wave drag coefficient to be added to the profile drag coefficient to give the total drag coefficient may be obtained from ESDU Aero W.S.00.03.04.