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	Estimation of critical Mach number for an aerofoil from its low-speed pressure distribution.
DATA Item	74008
KEYWORD	aerofoil, critical, distribution, mach, number, pressure, airfoil
ISBN	0 85679 061 3
ABSTRACT	ESDU 74008 gives curves (for inviscid incompressible flow) of critical Mach number at a point on the aerofoil surface plotted against the local pressure coefficient and the surface slope at that point. The method is based on first-order calculations but is also equivalent to second-order. If an exact method is used to calculate the pressure coefficient, a method is suggested of using ESDU 74008 to provide a comparable accuracy for the predicted critical Mach number.