국내 최대 기계 및 로봇 연구정보

공학설계D/B

공학설계D/B 게시판 내용
Volume Title	Aerodynamics
Volume No	CONTROLS AND FLAPS - Flaps - lift: aerofoils
DATA Title	Information on the use of Data Items on high-lift devices.
DATA Item	97002
KEYWORD	aerofoil, aileron, angle, control, device, drag, drooped, edge, elevator, flap, high, krueger, leading, lift, maximum, moment, pitching, plain, rudder, slat, slotted, split, vented, wing, zero, airfoil, kruger
ISBN	1 86246 004 3
ABSTRACT	ESDU 97002 is an introductory review of the methods provided in the Series for the estimation of the increments in the lift, pitching moment and drag over those of the plain aerofoil or wing (in the absence of a body) at zero lift due to the deployment of high-lift leading- and/or trailing-edge devices. The methods are largely empirical, being based on extensive wind-tunnel data. The lift and pitching moment increments vary only slightly with angle of attack provided the stalled region is avoided but a method is included that predicts the lift curve to maximum lift that is significantly more realistic than the assumption of a linear variation. It is assumed that the ratio of device chord to wing chord and dimensionless wing geometry are constant spanwise. Where that is not the case, values appropriate to the mid-device span may be used to average out the effects of spanwise variations. The accuracy of the methods is discussed in the individual documents; in the absence of an explicit statement, comparisons of experimental and predicted values for increments in lift, pitching moment and profile drag coefficients suggest that errors will be within 10 per cent in most cases. All the documents contain one or more worked examples to illustrate the use of the methods. ESDU 97003 provides methods for estimating the effect of fuselage interference on the increments in lift, pitching moment and drag predicted for the isolated wing.