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	Critical pressure coefficient and component of local Mach number normal to the surface isobar for a swept wing.
DATA Item	75027
KEYWORD	critical, flow, mach, number, pressure, supercritical, transonic, wing
ISBN	0 85679 131 8
ABSTRACT	ESDU 75027 gives a method, valuable in analysing measured pressure distribution data, for determining regions of supercritical flow on the wing. An equation (also given graphically) is derived for the Mach number of the flow component normal to an isobar by assuming that simple sweep theory can be applied locally; then the required Mach number is that normal to an infinite yawed wing of sweep equal to that of the isobar. An equation is also given (and again shown graphically) for the critical pressure coefficient derived when the Mach number normal to the isobar is unity. The method is thought to give answers not significantly different from those derived by more detailed analysis for incidences up to 10 degrees provided the wing does not combine low aspect ratio and high taper.