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	Approximate calculation of the pressure changes in two-dimensional supersonic flow.
DATA Item	AERO S.00.03.14
KEYWORD	aerofoil, busemann, corner, flow, oblique, pressure, ramp, shock, supersonic, wave, wedge, airfoil
ISBN
ABSTRACT	ESDU AERO S.00.03.14 gives a table of the first- and second-order Busemann coefficients (and their ratio) that appear in the equation for the pressure coefficient in terms of the deflection angle and its square for given values of the upstream Mach number. The second-order term in deflection is omitted in first-order theory; a sketch shows values of Mach number and deflection angle for which the values of pressure coefficient caculated by either first- or second-order theory depart by 5 per cent from those calculated using exact theory.