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	Increment in aerofoil profile drag coefficient due to the deployment of a single-slotted flap.
DATA Item	87005
KEYWORD	aerofoil, airfoil, device, drag, flap, high, lift, profile, program, slotted
ISBN	0 85679 598 4
ABSTRACT	ESDU 87005 gives a simple method for predicting the increment in drag at zero incidence for a flap positioned to maximise lift at stall. Using the limited number of experimental data available in the literature, a correlation method was developed that leads to a carpet graph of the variation of the increment with flap deflection angle and the ratio of the extended chord (due to flap deployment) to the basic aerofoil chord (with flap retracted). The carpet applies to aerofoils with maximum camber position between 0.2 and 0.65 of chord, and predicts the drag increment to within 20 per cent. The position of maximum camber was found to have a significant effect, and two similar carpets, one for maximum camber at 0.15 chord and one for it positioned between 0.7 and 0.8 of chord illustrate the trends with aerofoil and flap deployment geometry. The method does not apply if any leading-edge device is also deployed, but was found to apply for a straight-tapered unswept wing with full-span flaps. A worked example illustrates the use of the method, and the range of geometries for which experimental data were available and used to test the method is given. A Fortran program of the method is provided on disc (uncompiled) in the software volume as ESDUpac A8705.