국내 최대 기계 및 로봇 연구정보

공학설계D/B

공학설계D/B 게시판 내용
Volume Title	Aerodynamics
Volume No	CONTROLS AND FLAPS - Controls - lift, pitching moment, rolling moment, drag
DATA Title	Rudder sideforce, yawing moment and rolling moment control derivatives at low speeds: Y sub zeta, N sub zeta and L sub zeta.
DATA Item	87008
KEYWORD	control, deflection, derivative, moment, rolling, rudder, sideforce, yawing
ISBN	0 85679 601 8
ABSTRACT	ESDU 87008 predicts semi-empirically the sideforce due to rudder deflection and its point of action on the fin, from which the rolling and yawing derivatives due to rudder deflection are easily calculated. To obtain the sideforce, ESDU data for wing lift-curve slope and for plain control effectiveness are applied to the fin with appropriate corrections. The corrections allow for body interference (which depends on the body cross-section in the region of the fin) and for tailplane position on the fin between a T- tail and a tailplane at the fin/fuselage intersection. In addition, another correction is applied for a rudder that does not occupy the whole trailing-edge of the fin. Graphs show the accuracy of the predictions by comparing them with wind-tunnel data extracted from the literature. The ranges of geometry and Reynolds number covered by the tests are quoted. The data used were in the incidence range from 0 to 10 degrees, and the effect of any control gap was neglected. The sideforce derivative is thought to be predicted to within 0.04, the yawing moment derivative to within 0.02 and the rolling moment derivative to within 0.01. A worked example illustrates the use of the prediction method. A Fortran program of the method is provided on disc (uncompiled) in the software volume as ESDUpac A8708.