국내 최대 기계 및 로봇 연구정보

공학설계D/B

공학설계D/B 게시판 내용
Volume Title	Aerodynamics
Volume No	CONTROLS AND FLAPS - Flaps - lift: wings
DATA Title	Wing lift coefficient increment at zero angle of attack due to deployment of plain trailing-edge flaps at low speeds.
DATA Item	97011
KEYWORD	aerofoil, aileron, angle, control, device, elevator, flap, high, lift, plain, rudder, wing, zero, airfoil
ISBN	1 86246 010 8
ABSTRACT	ESDU 97011 provides an empirical method that applies to full- or part-span flaps on wings. It uses the method of ESDU 94028 to establish the lift increment due to deflection of the plain flap on an aerofoil having the geometry of the wing section at flap mid-span, taken to be representative of the wing, and then applies factors to allow for planform and part-span effects. An additional factor is required that is a function of flap deflection and the angle between the aerofoil upper surface and the aerofoil datum at the trailing-edge. Sketches compare experimental results from the literature with predictions by the method for both full- and part-span flaps on swept and unswept wings and show that predictions were accurate to within 15 per cent for 98 per cent of the test data. A worked example illustrates the use of the method.