![]() The camber is then said to be zero since it is the maximum distance between the chord line and the mean camber line. When the mean camber line and the chord line lie directly on top of each other the airfoil is symmetric. The distance then between the leading edge and trailing edge is simply the chord and it is denoted by the letter c. The chord line is a straight line drawn from the leading and trailing edges of the airfoil. The mean camber line is equidistant from the upper and lower cross section, essentially a dividing line where the thickness is equal above and below. Further investigating this cross-section, Figure 2, illustrates several design features.The most important design feature is the mean camber line, shown in figure as a dashed line spanning the length of the chord. When the vertical tail induces a rudder deflection the local flow is turned and results in a yawing motion.Īn airfoil is best visualized as the cross-section of a wing as shown in Figure 1. All control surfaces are in essence are airfoils. ![]() In aerospace applications airfoils are not only utilized on the wing. Other sources define airfoils to be any shape or surface designed to turn flow. NASA defines an airfoil to be a “streamlined surface designed in such a way that produces useful motion.” The useful motion being referred to in aerospace applications is lift or propulsion depending on where the airfoil is utilized.
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