XFOIL Version 6.96 Calculated polar for: GOE 493 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 ------ -------- --------- --------- -------- -------- -------- -17.500 -0.8436 0.08694 0.08389 -0.0737 1.0000 0.0074 -17.250 -0.8800 0.07791 0.07473 -0.0782 1.0000 0.0073 -17.000 -0.9182 0.06895 0.06562 -0.0827 1.0000 0.0073 -16.750 -0.9487 0.06151 0.05805 -0.0863 1.0000 0.0073 -16.500 -0.9707 0.05556 0.05199 -0.0891 1.0000 0.0074 -16.250 -0.9965 0.04943 0.04572 -0.0918 1.0000 0.0073 -16.000 -1.0156 0.04456 0.04074 -0.0936 1.0000 0.0073 -15.500 -1.0244 0.03628 0.03223 -0.0998 0.9986 0.0075 -15.250 -1.0148 0.03300 0.02883 -0.1038 0.9962 0.0076 -15.000 -1.0064 0.03010 0.02582 -0.1068 0.9916 0.0076 -14.750 -0.9937 0.02776 0.02339 -0.1096 0.9873 0.0078 -14.500 -0.9781 0.02576 0.02128 -0.1122 0.9836 0.0079 -14.250 -0.9645 0.02419 0.01962 -0.1134 0.9770 0.0080 -14.000 -0.9440 0.02271 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0.5311 0.00711 0.00158 -0.0932 0.5584 0.5286 1.500 0.5556 0.00715 0.00164 -0.0925 0.5507 0.5426 1.750 0.5811 0.00717 0.00169 -0.0920 0.5442 0.5583 2.000 0.6058 0.00721 0.00176 -0.0914 0.5370 0.5727 2.250 0.6306 0.00725 0.00182 -0.0908 0.5306 0.5859 2.500 0.6554 0.00729 0.00189 -0.0902 0.5232 0.5987 2.750 0.6776 0.00741 0.00198 -0.0891 0.5075 0.6119 3.000 0.7007 0.00748 0.00207 -0.0882 0.4978 0.6274 3.250 0.7233 0.00755 0.00217 -0.0871 0.4875 0.6439 3.750 0.7651 0.00774 0.00240 -0.0844 0.4583 0.6869 4.000 0.7799 0.00795 0.00255 -0.0818 0.4300 0.7110 4.250 0.7947 0.00815 0.00272 -0.0792 0.4049 0.7389 4.750 0.8247 0.00863 0.00315 -0.0741 0.3582 0.7911 5.000 0.8404 0.00883 0.00337 -0.0717 0.3404 0.8195 5.250 0.8554 0.00900 0.00359 -0.0692 0.3245 0.8576 5.500 0.8979 0.00928 0.00398 -0.0728 0.3003 0.9419 5.750 0.9542 0.00981 0.00439 -0.0798 0.2721 1.0000 6.000 0.9682 0.01017 0.00465 -0.0772 0.2513 1.0000 6.250 0.9800 0.01065 0.00497 -0.0743 0.2198 1.0000 6.500 0.9798 0.01163 0.00562 -0.0695 0.1583 1.0000 6.750 0.9898 0.01226 0.00611 -0.0665 0.1296 1.0000 7.000 0.9967 0.01307 0.00671 -0.0631 0.0906 1.0000 7.250 1.0103 0.01362 0.00717 -0.0609 0.0735 1.0000 7.500 1.0243 0.01418 0.00765 -0.0589 0.0589 1.0000 7.750 1.0379 0.01478 0.00817 -0.0568 0.0441 1.0000 8.000 1.0531 0.01532 0.00868 -0.0550 0.0372 1.0000 8.250 1.0702 0.01579 0.00914 -0.0536 0.0344 1.0000 8.500 1.0876 0.01625 0.00961 -0.0522 0.0329 1.0000 8.750 1.1047 0.01674 0.01011 -0.0509 0.0315 1.0000 9.000 1.1210 0.01729 0.01067 -0.0494 0.0303 1.0000 9.250 1.1372 0.01786 0.01126 -0.0480 0.0292 1.0000 9.500 1.1533 0.01846 0.01187 -0.0467 0.0282 1.0000 9.750 1.1703 0.01902 0.01246 -0.0455 0.0276 1.0000 10.000 1.1866 0.01962 0.01310 -0.0443 0.0270 1.0000 10.250 1.2025 0.02027 0.01377 -0.0431 0.0263 1.0000 10.500 1.2177 0.02098 0.01451 -0.0418 0.0256 1.0000 10.750 1.2323 0.02173 0.01528 -0.0406 0.0249 1.0000 11.000 1.2458 0.02257 0.01615 -0.0393 0.0241 1.0000 11.250 1.2584 0.02350 0.01711 -0.0379 0.0234 1.0000 11.500 1.2718 0.02439 0.01804 -0.0367 0.0229 1.0000 11.750 1.2867 0.02520 0.01888 -0.0357 0.0224 1.0000 12.000 1.3012 0.02604 0.01976 -0.0347 0.0217 1.0000 12.250 1.3138 0.02704 0.02080 -0.0336 0.0213 1.0000 12.500 1.3269 0.02802 0.02181 -0.0326 0.0205 1.0000 12.750 1.3388 0.02912 0.02295 -0.0315 0.0199 1.0000 13.000 1.3500 0.03028 0.02415 -0.0305 0.0194 1.0000 13.250 1.3594 0.03162 0.02551 -0.0294 0.0188 1.0000 13.500 1.3707 0.03283 0.02677 -0.0285 0.0182 1.0000 13.750 1.3823 0.03404 0.02803 -0.0277 0.0177 1.0000 14.000 1.3923 0.03543 0.02948 -0.0268 0.0172 1.0000 14.250 1.4019 0.03686 0.03095 -0.0260 0.0165 1.0000 14.500 1.4111 0.03835 0.03248 -0.0252 0.0160 1.0000 14.750 1.4192 0.03997 0.03412 -0.0245 0.0151 1.0000 15.000 1.4268 0.04168 0.03588 -0.0238 0.0146 1.0000 15.250 1.4342 0.04343 0.03769 -0.0232 0.0141 1.0000 15.500 1.4411 0.04526 0.03958 -0.0226 0.0136 1.0000 15.750 1.4472 0.04720 0.04157 -0.0220 0.0130 1.0000 16.000 1.4524 0.04926 0.04366 -0.0216 0.0124 1.0000 16.250 1.4569 0.05142 0.04587 -0.0211 0.0118 1.0000 16.500 1.4611 0.05367 0.04818 -0.0208 0.0114 1.0000 16.750 1.4643 0.05606 0.05064 -0.0205 0.0110 1.0000 17.000 1.4671 0.05850 0.05314 -0.0202 0.0107 1.0000 17.250 1.4691 0.06106 0.05576 -0.0201 0.0102 1.0000 17.500 1.4700 0.06379 0.05855 -0.0200 0.0098 1.0000 17.750 1.4700 0.06668 0.06150 -0.0200 0.0094 1.0000 18.000 1.4696 0.06965 0.06454 -0.0200 0.0091 1.0000 18.250 1.4692 0.07263 0.06760 -0.0202 0.0089 1.0000 18.500 1.4682 0.07573 0.07078 -0.0204 0.0087 1.0000 18.750 1.4662 0.07900 0.07412 -0.0207 0.0084 1.0000 19.000 1.4633 0.08242 0.07763 -0.0211 0.0082 1.0000 19.250 1.4598 0.08596 0.08125 -0.0217 0.0080 1.0000