Airfoil Design and Data by Prof. Dr. Richard Eppler (auth.)


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Therefore, This is, in merely many begin cases, a good little for less the abruptly, boundary if A layer. - and I-values with a 5 to the right of the decimal point. Some corners will exist also at the arc limits v; if the ex; for two adjacent arcs differ too much. The arc limits should, therefore, be specified between two points, which again causes a certain smoothing. In fact, the integration of the airfoil shape always uses the average ex* between two points. * is to increase continuously over a certain region of the airfoil, I 47 this can be achieved by introducing arc limits after every other point only.

5 v ex. 5 ~NACA65~_ oi~j j o Fig. 5 j x/c j I j 1 The NACA 65 -618 airfoil shape and velocity distributions cambered airfoil. 994. is merely to increase all which. 16). 6. Also. 17). v 2 and cx*-values because v4 are increased by 1. 8°. CPi L is expected input data lines are given on the next page. followed by the listing of the transcendental equation results and of the trailing edge iteration. The resulting airfoil shape and its velocity distributions are presented in Fig. 13. Obviously. 502 occurs.

Additional examples are given in the following table. unit for unit system Quantity to be measured time sec mass kg m/sec 2 acceleration force (= mass x acceleration) = stress / kinematic viscosity N = m kg/sec2 1Isec shear velocity viscosity m, kg, sec shear velocity kg/(m sec) m 2/sec The consequences of the new units L, V Rand PR are clear and simple. In an incompressible 49 problem, there is only one density p. It is selected as reference density PRo Then, P is measured in the unit PR' or P " 1.

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