Camber (aerodynamics)

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Topic: Camber (aerodynamics)

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	AERADE subject listing for AEROFOILS AND WINGS - General. Aerofoils at subcritical speeds - lift, pitching moment.
		The VGK program (see ESDU 96028 and 96029 in the Transonic Aerodynamics Series) was applied to a range of NACA aerofoils and also to aerofoils with complex camber lines to derive graphs of a reduction factor to be applied to the inviscid lift-curve slope from ESDU 72024.
		Because of the complexity of the flow approaching stall it is stated that the curves are approximate and that they should only be applied to âconventional aerofoils' with simple camber lines.
		ESDU AERO A.08.01.05 gives a curve that allows the ratio of the chordwise position of the aerodynamice centre in incompressible flow (h0) to that in incompressible inviscid flow (h0T) to be obtained for known ratios of incompressible to incompressible inviscid lift curve slopes, which may be obtained from ESDU AERO W.01.01.05.
	aerade.cranfield.ac.uk /subject-listing/esdu/ES55.html

	Shock Stall, High Speed Aerodynamics
		The precise effect is dependent on the geometry of the wing (camber, thickness ratio, etc.).
		The use of thin supercritical wing sections, low lift at operation point, and wing back sweep are among the most effective methods of postponing the shock stall to higher speeds.
		The increasing Mach number has some unfortunate effects on a wing: sudden increase of drag, corresponding decrease of lift, and longitudinal instability.
	aerodyn.org /HighSpeed/shock-stall.html

	Morphing Systems Overview
		Through morphing, the aerodynamics of the aircraft can be adapted to optimize performance in each segment by changing areas such as the camber of the airfoils and the twist distribution along the wing.
		Morphing, adaptable systems increase the usefulness and capabilities of a wide range of applications, and CRG has taken a leadership role in research involving morphing technologies.
		Morphing wing technology is considered to be a key component in next-generation unmanned aeronautical vehicles (UAVs) for military and civil application.
	www.crgrp.net /morphingsystems.htm (751 words)

	Kitebuilder Tech Sheets
		A very good essay discussing basic kite aerodynamics and terms such as aspect ratio, wing loading, washout, camber, billow, center of gravity, and stunt kite design.
		This bridle will tilt the kite backwards in turns and has several advantages; it tracks better in sharp turns and gives a better start and faster flying and therefore more power.
		The Information on the website is provided to give kite builders a better understanding of how to pick the best tube for the kite you are building.
	www.kitebuilder.com /techshee.htm (751 words)

	Dr Derek Bray, DAPS - DTC MSc Course Information
		As compared with a conventional airfoil a supercritical airfoil has a reduced amount of camber, an increased leading edge radius, smaller surface curvature on the suction side and a concave rear part of the pressure side.
		Whitcomb at NASA Langley also used advanced computational aerodynamics techniques at around the same time and came up with the "supercritical" section, so named because it was found that some supersonic flow could be tolerated without a significant drag increase.
		Supercritical, and especially shock-free designs often are very sensitive to Mach and C
	www.rmcs.cranfield.ac.uk /aeroxtra/dtcwingdesafftran.htm (366 words)

	Aerodynamics for Students
		The camber line is a polynomial function based on the desired ideal lift coefficient.
		The user inputs the desired section designation number and the number of surface data points required.
		These aerofoil sections are designed to produce laminar flow and low drag over a reasonable range of angles of attack.
	www.ae.su.oz.au /aero/naca45/naca45.html (366 words)

	Notre Dame Micro Aerial Vehicle Development Group
		Current work in the low Reynolds number aerodynamics project include the wind tunnel testing of low aspect ratio wings with varying camber configurations, including reflex airfoil shapes that neutralize the pitching moment in tailless aircraft.
		The design of vehicles which operate at Reynolds numbers below 200,000 is difficult because many of the simplifications of the governing equations which are valid for large Reynolds numbers are not valid for MAV flight regimes.
		The Reynolds number is a ratio of inertial forces to viscous forces and varies from a few thousands for insects to several millions for commercial aircraft (see figure below).
	www.nd.edu /~mav/research.htm (789 words)

	Aerospaceweb.org UCAV - Aerodynamics
		Thus, the airfoils used on both the inboard and outboard wings must have little camber to reduce pitching moment as well as a small thickness to chord ratio (t/c) and leading edge radius to insure a high M
		The NACA 66-008 was chosen for the outboard wing because (a) its critical Mach number is less than the maximum Mach number specified by the RFP and (b) its maximum thickness is closer to the middle which better suits the structural design.
		An initial LE angle of 48° was selected since it is similar to that used on the wing of the F-22 fighter.
	www.aerospaceweb.org /design/ucav/aerodynamics.shtml (563 words)

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Topic: Camber (aerodynamics)

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