XFOIL Version 6.96 Calculated polar for: GOE 683 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.1608 0.06610 0.06207 -0.0748 1.0000 0.0328 -19.500 -1.1823 0.06028 0.05612 -0.0776 1.0000 0.0330 -19.250 -1.1993 0.05515 0.05087 -0.0798 1.0000 0.0331 -19.000 -1.2083 0.05113 0.04675 -0.0815 1.0000 0.0337 -18.750 -1.2192 0.04701 0.04252 -0.0830 1.0000 0.0337 -18.500 -1.2232 0.04383 0.03925 -0.0839 1.0000 0.0340 -18.250 -1.2305 0.04048 0.03579 -0.0846 1.0000 0.0340 -18.000 -1.2272 0.03837 0.03360 -0.0847 1.0000 0.0345 -17.750 -1.2310 0.03572 0.03089 -0.0846 1.0000 0.0349 -17.500 -1.2312 0.03358 0.02868 -0.0841 1.0000 0.0352 -17.250 -1.2300 0.03171 0.02675 -0.0833 1.0000 0.0356 -17.000 -1.2274 0.03009 0.02508 -0.0822 1.0000 0.0358 -16.750 -1.2233 0.02869 0.02364 -0.0808 1.0000 0.0363 -16.500 -1.2181 0.02747 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0.6833 3.000 0.4573 0.00850 0.00286 -0.0006 0.3639 0.7357 3.500 0.6248 0.00904 0.00390 -0.0246 0.3518 0.9021 3.750 0.6461 0.00920 0.00404 -0.0232 0.3477 0.9115 4.000 0.6650 0.00942 0.00424 -0.0212 0.3439 0.9213 4.250 0.6850 0.00966 0.00447 -0.0195 0.3398 0.9282 4.500 0.7157 0.00993 0.00473 -0.0200 0.3362 0.9329 4.750 0.7198 0.01001 0.00482 -0.0149 0.3329 0.9406 5.000 0.7544 0.01027 0.00505 -0.0164 0.3283 0.9420 5.250 0.7883 0.01056 0.00531 -0.0178 0.3236 0.9437 5.500 0.8229 0.01082 0.00557 -0.0193 0.3201 0.9461 5.750 0.8472 0.01103 0.00577 -0.0186 0.3166 0.9498 6.000 0.8577 0.01124 0.00597 -0.0150 0.3122 0.9553 6.250 0.8914 0.01152 0.00622 -0.0164 0.3064 0.9564 6.500 0.9219 0.01170 0.00640 -0.0172 0.3023 0.9575 6.750 0.9450 0.01186 0.00655 -0.0164 0.2968 0.9588 7.000 0.9649 0.01205 0.00671 -0.0151 0.2922 0.9605 7.250 0.9817 0.01222 0.00688 -0.0130 0.2885 0.9629 7.500 0.9751 0.01236 0.00704 -0.0061 0.2863 0.9679 7.750 1.0004 0.01252 0.00720 -0.0059 0.2821 0.9684 8.000 1.0244 0.01274 0.00741 -0.0056 0.2766 0.9691 8.250 1.0481 0.01298 0.00764 -0.0053 0.2722 0.9699 8.500 1.0707 0.01321 0.00786 -0.0047 0.2665 0.9708 8.750 1.0901 0.01352 0.00815 -0.0036 0.2601 0.9718 9.000 1.1087 0.01382 0.00845 -0.0024 0.2546 0.9731 9.250 1.1250 0.01416 0.00877 -0.0008 0.2479 0.9746 9.500 1.1359 0.01459 0.00919 0.0017 0.2423 0.9767 9.750 1.1332 0.01511 0.00971 0.0071 0.2373 0.9805 10.000 1.1526 0.01559 0.01017 0.0076 0.2290 0.9810 10.250 1.1716 0.01609 0.01066 0.0081 0.2220 0.9815 10.500 1.1891 0.01669 0.01124 0.0087 0.2139 0.9822 10.750 1.2057 0.01735 0.01189 0.0094 0.2066 0.9829 11.000 1.2203 0.01811 0.01262 0.0103 0.1983 0.9837 11.250 1.2286 0.01924 0.01370 0.0117 0.1837 0.9847 11.500 1.2285 0.02100 0.01535 0.0135 0.1602 0.9863 11.750 1.2210 0.02314 0.01738 0.0161 0.1390 0.9878 12.000 1.2208 0.02487 0.01907 0.0180 0.1289 0.9889 12.250 1.2272 0.02618 0.02040 0.0193 0.1251 0.9899 12.500 1.2310 0.02767 0.02190 0.0209 0.1214 0.9908 12.750 1.2340 0.02914 0.02340 0.0226 0.1187 0.9918 13.000 1.2427 0.03051 0.02481 0.0234 0.1168 0.9925 13.250 1.2523 0.03198 0.02631 0.0236 0.1145 0.9928 13.500 1.2624 0.03341 0.02779 0.0238 0.1137 0.9931 13.750 1.2659 0.03543 0.02982 0.0243 0.1103 0.9935 14.000 1.2705 0.03736 0.03179 0.0246 0.1079 0.9939 14.250 1.2768 0.03916 0.03363 0.0249 0.1061 0.9942 14.500 1.2846 0.04085 0.03537 0.0251 0.1049 0.9946 14.750 1.2918 0.04260 0.03718 0.0253 0.1040 0.9949 15.000 1.2978 0.04448 0.03911 0.0255 0.1033 0.9953 15.250 1.2999 0.04673 0.04140 0.0258 0.1010 0.9956 15.500 1.3036 0.04885 0.04356 0.0260 0.0998 0.9959 15.750 1.3047 0.05128 0.04604 0.0261 0.0985 0.9962 16.000 1.3056 0.05385 0.04866 0.0261 0.0972 0.9966 16.250 1.3072 0.05640 0.05126 0.0259 0.0954 0.9969 16.500 1.3113 0.05864 0.05356 0.0258 0.0943 0.9972 16.750 1.3148 0.06090 0.05588 0.0258 0.0936 0.9974 17.000 1.3164 0.06341 0.05845 0.0257 0.0920 0.9977 17.250 1.3163 0.06612 0.06120 0.0255 0.0898 0.9979 17.500 1.3108 0.06946 0.06455 0.0253 0.0859 0.9981 17.750 1.3100 0.07234 0.06748 0.0250 0.0833 0.9983 18.000 1.3058 0.07561 0.07077 0.0246 0.0782 0.9984 18.250 1.3004 0.07909 0.07427 0.0242 0.0745 0.9986 18.500 1.2888 0.08333 0.07852 0.0235 0.0684 0.9988 18.750 1.2831 0.08692 0.08212 0.0229 0.0648 0.9989