By Hermann T. Schlichting, Erich A. Truckenbrodt (transl. by Heinrich J. Ramm)
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Additional info for Aerodynamics of the Airplane
The agreement is very good for small camber. For larger camber, some deviations can be seen. Of particular interest is the largest velocity on the profile at a = 0. It occurs at the profile center t = 0 and is obtained from Eq. (2-38) as wCmax=wo,1 1 +4 k (2-39a) + EL L (2-39b) =Woo 1 7r ) These equations allow a very simple estimation of the maximum velocity on a very thin circular-arc profile with smooth leading-edge flow. Inclined symmetric Joukowsky profile The symmetric Joukowsky profile may serve as a further example.
The resulting flow (c) = (a) + (b) does not yet produce lift on the plate because identical flow conditions exist at the leading and trailing edges. The front stagnation point is located on the lower surface and the rear stagnation point on the upper surface of the plate. U" a 4a-C b v00 z plane plane Figure 2-8 Flow about an inclined flat plate. (a) Flat plate in parallel flow. (b) Flat plate in normal (stagnation) flow. (c) Inclined flat plate without lift, (c) = (a) + (b). (d) Pure circulation flow.
2-3-2 Inclined Flat Plate The simplest case of a lifting-airfoil profile is the inclined flat plate. The angle between the direction of the incident flow and the direction of the plate is called angle of attack a of the plate. The flow about the inclined flat plate is obtained as shown in Fig. 2-8, by superposition of the plate in parallel flow (a) and the plate in normal flow (b). The resulting flow (c) = (a) + (b) does not yet produce lift on the plate because identical flow conditions exist at the leading and trailing edges.