국내 최대 기계 및 로봇 연구정보

공학설계D/B

공학설계D/B 게시판 내용
Volume Title	Aerodynamics
Volume No	BODIES - Drag
DATA Title	External wave drag at zero incidence in inviscid flow of simple ducted forebodies and truncated afterbodies.
DATA Item	Aero B.S.02.03.02
KEYWORD	afterbody, axisymmetric, body, drag, ducted, flow, forebody, supersonic, wave
ISBN
ABSTRACT	ESDU Aero B.S.02.03.02 give curves plotting the wave drag coefficient of circular cross section ducted or pointed forebodies and truncated or pointed afterbodies as a function of freestream Mach number, body length, and minimum and maximum cross-section radii. The bodies are conical or bodies of revolution generated by parabolic arcs but the data for the latter bodies are applicable within the likely accuracy to bodies generated using circular arcs. The data were obtained theoretically; for the forebodies it is assumed there is undisturbed flow ahead of the nose and no spillage, and for the afterbodies that the flow is parallel to the body axis and there is no interference from any forebody. Equations are also given, derived from slender-body theory, for the wave drag coefficient of pointed conical and parabolic afterbodies. The wave drag of a forebody or afterbody of elliptical cross section is less than for the corresponding body of circular cross section and the same cross-sectional area distribution. Curves plot that difference for conical or parabolic ducted forebodies or truncated afterbodies as a function of freestream Mach number, body length, cross section geometry, the maximum cross-sectional area, and the nose or base area. The curves were derived using slender-body theory and assume the flow is everywhere supersonic. Interference wave drag when any midbody separating the forebody from the afterbody is short may be obtained from ESDU Aero B.S.02.03.08. Worked examples illustrate the use of the data.