By Prof. Dr. Richard Eppler (auth.)
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Extra info for Airfoil Design and Data
8 has been specified, which yields a concave recovery function which, it will turn out, is advantageous for boundary layer reasons. One example from these many airfoils, 997, is given in detail. The input lines are listed below and the airfoil shape and two velocity distributions are shown in Fig. 16. 3 0 45 ex. 5 OK997 17% I o Fig. 17. These curves serve as a rough guide, in many cases, to estimate the effect of a change of rx* on the thickness. Several other details can be explained using airfoil 997 in Fig.
These are the segments next to the leading edge on both surfaces, SiL on the upper and SiL+1 on the lower surface. If ITMOD changed; if ITMOD = 9, both a i : until Ks = KR is achieved. = 7, only a i: is changed; if ITMOD = 8, only a i: +1 is and a i : +1 are changed simultaneously in opposite directions ITMOD =3 and ITMOD =9 are appropriate for symmetrical airfoils. By means of such iteration modes, the impossible trailing edge of airfoil 990 can be corrected. Airfoil 991 uses the same input as airfoil 990 but, in the F-words F11 and F12 of the TRA2-line, ITMOD = 6 and KR = 0 are specified.
The resulting airfoil, 993, and its most important velocity distributions are shown in Fig. 10. 5 ot: o Fig. 54° is also plotted. 56° < ex;. 00% for the NACA airfoil. The shapes of both airfoils are very similar except in a very small region near the leading edge. The velocity also differs slightly near the beginning of the main recovery. The redesigned airfoil has a very definite beginning of the recovery, which is more gradual on the NACA airfoil. It is of interest whether this is a numerical smoothing effect of the analysis method.