By Prof. Dr. Richard Eppler (auth.)
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Extra info for Airfoil Design and Data
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. 5. the on the upper surface and at x on the lower surface.
5, as mentioned above. 11. 1) always has the tendency towards a 30 more concave recovery function. 5. In the symmetrical problem, the leading edge must be at 180° or this is already known, the input must be \1 2 = 30 and specified = KH KH The insert it. In although none is Rl input the same expected \1 2 = O. sense, as a = N/2 = 30. Although \1 2 The program will closure discussed in compute the contribution b). If this length A expectation correct ="5: = is 4 is realized, 0 will result. The identification number for this airfoil is 990.
062 1. 092 1. 186 1. 169 1. 157 1. 144 1. 128 1. 107 1. 258 1. 040 1. 982 1. 704 1. 821 1. 144 1. 157 1. 169 1. 178 1. 139 1. 135 1. 093 1. 099 1. 062 1. 062 1. 030 1. 993 1. 035 1. 084 33 if the velocity distributions are plotted, the printed values are not of much interest. Such plots can be initiated by a DIAG-line. 15). What can be done in order to obtain a reasonable airfoil? There are two ways. The first possibility is to specify less pressure recovery, for example, higher wand w in the TRA2 line.