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	The mean skin friction coefficient for a rough flat plate with a turbulent two-dimensional boundary layer in compressible adiabatic flow, with application to wedges, cylinders and cones.
DATA Item	73016
KEYWORD	adiabatic, boundary, cone, cylinder, drag, flat, flow, friction, layer, plate, rough, skin, smooth, supersonic, turbulent, wedge
ISBN	0 85679 040 0
ABSTRACT	ESDU 73016 gives curves and an equation for the value of Reynolds number based on distance along the plate above which an increase in roughness height will not affect skin friction drag. Also given are curves for the mean skin friction on an aerodynamically smooth, or a fully rough, plate at zero incidence for Mach numbers from 0 to 5 for various roughness heights. The use of the data for cylinders, and for cones and wedges in supersonic flow, is explained. Comparison with experimental data shows an r.m.s. error of 3 per cent in incompressible flow rising to 9 per cent for compressible adiabatic flow.