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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