국내 최대 기계 및 로봇 연구정보

공학설계D/B

공학설계D/B 게시판 내용
Volume Title	Aerodynamics
Volume No	GENERAL - Organisation, properties of gases, isentropic flow and shock waves.
DATA Title	Solutions to the Prandtl-Meyer expansion relations for a range of specific heat ratios: pressure coefficient and maximum flow deflection angle.
DATA Item	AERO 00.03.31
KEYWORD	angle, corner, deflection, expansion, flow, meyer, prandtl, pressure, supersonic, wave
ISBN
ABSTRACT	ESDU AERO 00.03.31 gives a curves, based on a hypersonic similarity solution to the Prandtl-Meyer expansion relations. that allow the static pressure difference across the expension to be evaluated knowing only the upstream Mach number, gamma, and flow deflection angle. The equation for the curves is given. A sketch shows boundaries, in terms of the upstream Mach number and the ratio of flow deflection angle to the maximum, of errors of 1, 2, 3 and 4 per cent incurred using those curves compared with exact solutions. Another graph plots the maximum flow deflection angle against upstream Mach number from 1 to 10 and gamma from 1 (to aid interpolation) to 1.67 and the exact equation for those curves is given.