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	Inviscid supersonic flow past cones at zero incidence: (ii) surface pressure coefficient and shock angle for circular cones.
DATA Item	AERO S.00.03.13
KEYWORD	angle, cone, flow, pressure, shock, supersonic, surface, wave
ISBN
ABSTRACT	ESDU AERO S.00.03.13, which is one of a group of four, presents data for the surface pressure coefficient on a sharp-nosed right-circular cone. The data are given in graphical form for upstream Mach numbers from 1 to 4 for cones with semi-vertex angle from 0 to 42.5 degrees and were obtained from an exact solution of the conical flow equations. They apply only when the flow is fully supersonic and a curve is given defining the limit when the flow on the cone is just at a Mach number of unity.