국내 최대 기계 및 로봇 연구정보

공학설계D/B

공학설계D/B 게시판 내용
Volume Title	Transonic Aerodynamics
Volume No	Axisymmetric bodies: drag rise. Axisymmetric forebodies: wave drag, pressure distribution.
DATA Title	A method for estimating drag-rise Mach number at zero incidence of smooth or bumpy non-ducted axisymmetric bodies without or with fins.
DATA Item	74013
KEYWORD	axisymmetric, body, drag, flow, mach, number, rise, transonic, wave
ISBN	0 85679 119 9
ABSTRACT	ESDU 74013 gives a method of predicting when the shock first appears downstream of the point of maximum cross section, either on first being formed or on moving from an upstream station. It has been observed experimentally that this condition corresponds to the rapid increase in shock-wave drag. The fins are taken into account as distributed cross-sectional area to give an equivalent body, and the method relies on computing an incompressible velocity distribution from the body geometry. Comparison of the method with experimental data shows it predicts the drag-rise Mach number to within 0.015.