XFOIL Version 6.96 Calculated polar for: GOE 417A (GEW. PLATTE) AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.250 -0.3918 0.12889 0.12649 -0.0171 1.0000 0.0094 -11.000 -0.3892 0.12659 0.12421 -0.0169 1.0000 0.0095 -10.750 -0.3874 0.12417 0.12181 -0.0166 1.0000 0.0095 -10.500 -0.3821 0.12307 0.12071 -0.0161 1.0000 0.0104 -10.250 -0.3724 0.11997 0.11761 -0.0180 0.9994 0.0113 -10.000 -0.3626 0.11646 0.11410 -0.0203 0.9985 0.0115 -9.750 -0.3520 0.11318 0.11081 -0.0227 0.9974 0.0114 -9.500 -0.3410 0.10982 0.10746 -0.0252 0.9960 0.0121 -9.250 -0.3289 0.10698 0.10462 -0.0276 0.9948 0.0124 -9.000 -0.3177 0.10401 0.10165 -0.0298 0.9935 0.0125 -8.750 -0.3075 0.10121 0.09885 -0.0318 0.9917 0.0127 -8.500 -0.2956 0.09853 0.09617 -0.0340 0.9897 0.0141 -8.250 -0.2833 0.09541 0.09305 -0.0369 0.9876 0.0139 -8.000 -0.2659 0.09305 0.09068 -0.0401 0.9858 0.0171 -7.750 -0.2528 0.08991 0.08753 -0.0433 0.9824 0.0172 -7.500 -0.2375 0.08660 0.08421 -0.0468 0.9785 0.0173 -7.250 -0.2143 0.08281 0.08040 -0.0529 0.9760 0.0175 -6.750 -0.1801 0.07694 0.07452 -0.0585 0.9702 0.0181 -6.500 -0.1593 0.07420 0.07177 -0.0621 0.9676 0.0191 -6.250 -0.1331 0.07101 0.06854 -0.0671 0.9657 0.0200 -6.000 -0.1017 0.06765 0.06513 -0.0735 0.9641 0.0202 -5.750 -0.0743 0.06516 0.06258 -0.0787 0.9593 0.0203 -5.500 -0.0439 0.06241 0.05977 -0.0841 0.9565 0.0204 -5.250 -0.0080 0.05958 0.05687 -0.0904 0.9545 0.0204 -5.000 0.0276 0.05659 0.05381 -0.0961 0.9530 0.0204 -4.750 0.0423 0.05336 0.05059 -0.0961 0.9492 0.0205 -4.500 0.0614 0.05067 0.04788 -0.0971 0.9449 0.0206 -4.250 0.0878 0.04803 0.04520 -0.0998 0.9420 0.0207 -4.000 0.1184 0.04555 0.04267 -0.1033 0.9397 0.0209 -3.750 0.1378 0.04371 0.04081 -0.1038 0.9338 0.0211 -3.500 0.1654 0.04164 0.03869 -0.1059 0.9300 0.0215 -3.250 0.1967 0.03952 0.03650 -0.1087 0.9270 0.0219 -3.000 0.2194 0.03780 0.03472 -0.1092 0.9200 0.0222 -2.750 0.2504 0.03588 0.03273 -0.1113 0.9137 0.0227 -2.500 0.2765 0.03439 0.03116 -0.1119 0.9056 0.0231 -2.250 0.3069 0.03272 0.02941 -0.1134 0.8987 0.0233 -2.000 0.3320 0.03127 0.02787 -0.1135 0.8904 0.0233 -1.750 0.3613 0.02973 0.02623 -0.1144 0.8815 0.0234 -1.500 0.3871 0.02834 0.02474 -0.1144 0.8687 0.0234 -1.250 0.4151 0.02697 0.02324 -0.1146 0.8517 0.0234 -1.000 0.4422 0.02568 0.02177 -0.1146 0.8226 0.0235 -0.750 0.4680 0.02456 0.02034 -0.1140 0.7750 0.0235 -0.500 0.4899 0.02364 0.01912 -0.1126 0.7379 0.0235 -0.250 0.5119 0.02272 0.01797 -0.1111 0.7130 0.0236 0.000 0.5339 0.02185 0.01687 -0.1096 0.6887 0.0236 0.250 0.5552 0.02103 0.01586 -0.1081 0.6652 0.0236 0.500 0.5744 0.01965 0.01432 -0.1066 0.6418 0.0238 0.750 0.5924 0.01863 0.01317 -0.1051 0.6154 0.0240 1.000 0.6107 0.01799 0.01237 -0.1035 0.5857 0.0245 1.250 0.6311 0.01745 0.01167 -0.1020 0.5613 0.0249 1.500 0.6528 0.01692 0.01097 -0.1005 0.5422 0.0253 1.750 0.6748 0.01642 0.01031 -0.0991 0.5237 0.0255 2.000 0.6973 0.01595 0.00970 -0.0978 0.5065 0.0258 2.250 0.7202 0.01552 0.00913 -0.0965 0.4908 0.0262 2.500 0.7427 0.01522 0.00866 -0.0950 0.4683 0.0269 2.750 0.7651 0.01521 0.00843 -0.0934 0.4356 0.0276 3.000 0.7851 0.01523 0.00814 -0.0915 0.3822 0.0277 3.250 0.8020 0.01545 0.00791 -0.0892 0.3005 0.0278 3.500 0.8193 0.01573 0.00775 -0.0871 0.2284 0.0279 3.750 0.8412 0.01560 0.00745 -0.0858 0.2073 0.0279 4.000 0.8639 0.01541 0.00712 -0.0846 0.1938 0.0280 6.000 1.0363 0.01552 0.00645 -0.0749 0.0372 0.0407 6.250 1.0575 0.01564 0.00658 -0.0734 0.0341 0.0321 6.500 1.0775 0.01582 0.00678 -0.0718 0.0316 0.0304 6.750 1.0967 0.01613 0.00711 -0.0700 0.0290 0.0292 7.000 1.1161 0.01642 0.00745 -0.0684 0.0279 0.0286 7.250 1.1355 0.01668 0.00776 -0.0667 0.0272 0.0284 7.500 1.1543 0.01697 0.00812 -0.0650 0.0263 0.0283 7.750 1.1719 0.01726 0.00848 -0.0630 0.0253 0.0286 8.000 1.1887 0.01758 0.00885 -0.0609 0.0243 0.0293 8.250 1.2050 0.01794 0.00923 -0.0587 0.0232 0.0309 8.500 1.2204 0.01840 0.00972 -0.0564 0.0222 0.0338 8.750 1.2339 0.01900 0.01035 -0.0538 0.0213 0.0350 9.000 1.2435 0.01987 0.01131 -0.0505 0.0204 0.0355 9.250 1.2588 0.02035 0.01185 -0.0483 0.0201 0.0361 9.500 1.2735 0.02086 0.01243 -0.0461 0.0196 0.0379 9.750 1.2876 0.02139 0.01308 -0.0438 0.0191 0.1178 10.000 1.4528 0.02269 0.01556 -0.0762 0.0158 1.0000 10.250 1.4586 0.02351 0.01642 -0.0724 0.0151 1.0000 10.500 1.4678 0.02416 0.01715 -0.0692 0.0147 1.0000 10.750 1.4780 0.02478 0.01786 -0.0662 0.0143 1.0000 11.000 1.4897 0.02532 0.01849 -0.0636 0.0136 1.0000 11.250 1.5005 0.02594 0.01918 -0.0610 0.0129 1.0000 11.500 1.5121 0.02651 0.01980 -0.0585 0.0122 1.0000 11.750 1.5225 0.02719 0.02053 -0.0560 0.0117 1.0000 12.000 1.5314 0.02799 0.02138 -0.0533 0.0112 1.0000 12.250 1.5362 0.02913 0.02259 -0.0503 0.0106 1.0000 12.500 1.5425 0.03020 0.02378 -0.0475 0.0104 1.0000 12.750 1.5486 0.03131 0.02502 -0.0448 0.0099 1.0000 13.000 1.5553 0.03241 0.02623 -0.0424 0.0094 1.0000 13.250 1.5599 0.03372 0.02765 -0.0398 0.0090 1.0000 13.500 1.5668 0.03486 0.02887 -0.0377 0.0084 1.0000 13.750 1.5708 0.03630 0.03040 -0.0355 0.0082 1.0000 14.000 1.5737 0.03791 0.03210 -0.0334 0.0079 1.0000 14.250 1.5736 0.03986 0.03414 -0.0314 0.0074 1.0000 14.500 1.5720 0.04210 0.03651 -0.0295 0.0071 1.0000 14.750 1.5718 0.04429 0.03885 -0.0280 0.0069 1.0000 15.000 1.5671 0.04713 0.04184 -0.0267 0.0068 1.0000 15.250 1.5633 0.05003 0.04489 -0.0257 0.0066 1.0000 15.500 1.5581 0.05323 0.04824 -0.0251 0.0064 1.0000 15.750 1.5517 0.05677 0.05193 -0.0249 0.0062 1.0000 16.000 1.5457 0.06046 0.05576 -0.0250 0.0060 1.0000 16.250 1.5416 0.06401 0.05943 -0.0254 0.0059 1.0000 16.500 1.5295 0.06894 0.06454 -0.0264 0.0059 1.0000 16.750 1.5214 0.07348 0.06921 -0.0276 0.0057 1.0000 17.000 1.5120 0.07837 0.07422 -0.0290 0.0055 1.0000 17.250 1.4953 0.08463 0.08064 -0.0312 0.0055 1.0000 17.500 1.4801 0.09086 0.08703 -0.0336 0.0055 1.0000 17.750 1.4626 0.09774 0.09405 -0.0364 0.0054 1.0000 18.000 1.4418 0.10554 0.10202 -0.0399 0.0054 1.0000 18.250 1.4230 0.11328 0.10990 -0.0436 0.0053 1.0000 18.500 1.4048 0.12108 0.11784 -0.0473 0.0053 1.0000 18.750 1.3822 0.13007 0.12699 -0.0519 0.0054 1.0000 19.000 1.3600 0.13929 0.13635 -0.0567 0.0054 1.0000