국내 최대 기계 및 로봇 연구정보

공학설계D/B

공학설계D/B 게시판 내용
Volume Title	Aerodynamics
Volume No	CONTROLS AND FLAPS - Flaps - lift curve, pitching moment. Flaps - drag.
DATA Title	Computer program for estimation of lift curve to maximum lift for wing-fuselage combinations with high-lift devices at low speeds.
DATA Item	99031
KEYWORD	aerofoil, airfoil, curve, lift, slope, maximum, device, flap, high, increment, plain, slotted, split, trailing, edge, kruger, krueger, leading, slat, program, vented, camber, twist, wing, combination, fuselage, zero, angle, attack, interference, incidence
ISBN	1 86246 099 X
ABSTRACT	The construction of the input file for the program, based on 22 ESDU documents, is described. The program applies to aerofoils, wings and wing-fuselage combinations with leading-edge and trailing-edge devices deployed. Sketches from the original ESDU documents from which prediction methods have been taken are reproduced to aid the user in determining geometric parameters but the underlying methods are not repeated. Calculations can be made for the aerofoil and wing when there are no devices deployed but the prediction of the shape of the non-linear part of the lift curve should be treated with caution because it employs a simple technique developed for use when high-lift devices are deployed. Calculations may be made at number of Mach number and Reynolds number pairs. At each pair there may be one or more settings of the leading-edge device. At each leading-edge device setting there may be one or more trailing-edge flap settings. The method is intended for freestream Mach numbers up to about 0.25. No allowance is made for ground effect. The user may select from a number of different types of run. A run may be restricted to the calculation of the lift coefficient at zero angle of attack or to the calculation of the increment in maximum lift coefficient. There is provision for user-defined lift coefficients to be used for the basic aerofoil, wing or wing-fuselage combination in place of the calculated values. There may be different types of high-lift devices over different spanwise segments of a wing. For example, there could be a slotted trailing-edge flap panel over the inboard part of a wing and a plain trailing-edge flap panel outboard. In the case of leading-edge devices, if the calculation is to include the prediction of maximum lift coefficient, there can be only a single device panel which must extend to the wing tip. An auxiliary program allows the prior calculation of the spanwise position of the section of the basic wing that has the peak loading due to angle of attack. It is necessary to know that section because full runs of the main program for wings and wing-fuselage combinations require its geometry.