XFOIL Version 6.96 Calculated polar for: GRUMMAN K-3 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.750 -0.9672 0.09534 0.08903 -0.0733 0.9999 0.0578 -18.500 -0.9766 0.09115 0.08473 -0.0746 0.9999 0.0586 -18.250 -0.9858 0.08709 0.08055 -0.0757 0.9999 0.0593 -18.000 -0.9943 0.08324 0.07655 -0.0767 0.9999 0.0600 -17.750 -0.9981 0.08025 0.07351 -0.0771 0.9999 0.0607 -17.500 -1.0009 0.07750 0.07073 -0.0773 0.9999 0.0613 -17.250 -1.0042 0.07474 0.06794 -0.0775 0.9999 0.0621 -17.000 -1.0080 0.07196 0.06509 -0.0776 0.9999 0.0629 -16.750 -1.0116 0.06928 0.06235 -0.0775 0.9999 0.0638 -16.500 -1.0152 0.06668 0.05965 -0.0774 0.9999 0.0648 -16.250 -1.0186 0.06415 0.05702 -0.0771 0.9999 0.0658 -16.000 -1.0208 0.06194 0.05477 -0.0765 0.9999 0.0667 -15.750 -1.0233 0.05978 0.05261 -0.0759 0.9999 0.0676 -15.500 -1.0258 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0.01074 -0.1236 0.8765 0.5433 -1.250 0.2980 0.01724 0.01073 -0.1252 0.8757 0.5518 -1.000 0.3072 0.01778 0.01132 -0.1218 0.8665 0.5569 -0.750 0.3420 0.01756 0.01119 -0.1225 0.8631 0.5620 -0.500 0.3984 0.01632 0.00997 -0.1267 0.8591 0.5672 -0.250 0.4339 0.01545 0.00908 -0.1269 0.8434 0.5717 0.000 0.4697 0.01484 0.00843 -0.1276 0.8271 0.5759 0.250 0.5097 0.01443 0.00804 -0.1294 0.8173 0.5791 0.500 0.5354 0.01438 0.00807 -0.1286 0.8057 0.5819 0.750 0.5671 0.01424 0.00797 -0.1289 0.7936 0.5848 1.000 0.6027 0.01403 0.00777 -0.1299 0.7780 0.5882 1.250 0.6347 0.01390 0.00763 -0.1302 0.7556 0.5919 1.500 0.6719 0.01374 0.00734 -0.1315 0.7178 0.5955 1.750 0.7010 0.01400 0.00697 -0.1309 0.5943 0.5987 2.000 0.7063 0.01505 0.00734 -0.1262 0.4805 0.6013 2.250 0.7123 0.01599 0.00786 -0.1219 0.3946 0.6037 2.500 0.7222 0.01682 0.00836 -0.1185 0.3261 0.6064 2.750 0.7346 0.01751 0.00880 -0.1155 0.2741 0.6092 3.000 0.7502 0.01811 0.00921 -0.1132 0.2362 0.6121 3.250 0.7682 0.01866 0.00960 -0.1114 0.2089 0.6152 3.500 0.7883 0.01915 0.00999 -0.1100 0.1893 0.6183 3.750 0.8099 0.01964 0.01039 -0.1089 0.1742 0.6218 4.000 0.8325 0.02009 0.01079 -0.1080 0.1624 0.6250 4.250 0.8539 0.02053 0.01124 -0.1067 0.1529 0.6278 4.750 0.8975 0.02146 0.01214 -0.1045 0.1354 0.6336 5.000 0.9194 0.02195 0.01260 -0.1034 0.1278 0.6367 5.250 0.9416 0.02242 0.01306 -0.1025 0.1206 0.6402 5.500 0.9642 0.02288 0.01352 -0.1015 0.1143 0.6440 5.750 0.9860 0.02342 0.01400 -0.1006 0.1082 0.6477 6.000 1.0080 0.02384 0.01450 -0.0995 0.1020 0.6507 6.250 1.0291 0.02434 0.01501 -0.0983 0.0964 0.6538 6.500 1.0505 0.02483 0.01553 -0.0973 0.0905 0.6571 6.750 1.0721 0.02533 0.01607 -0.0962 0.0846 0.6606 7.000 1.0931 0.02587 0.01661 -0.0951 0.0788 0.6643 7.250 1.1141 0.02645 0.01718 -0.0941 0.0730 0.6683 7.500 1.1346 0.02705 0.01778 -0.0929 0.0672 0.6721 7.750 1.1541 0.02766 0.01843 -0.0916 0.0616 0.6758 8.000 1.1732 0.02833 0.01913 -0.0902 0.0563 0.6797 8.250 1.1917 0.02906 0.01989 -0.0889 0.0518 0.6838 8.500 1.2098 0.02985 0.02070 -0.0875 0.0479 0.6880 8.750 1.2274 0.03070 0.02155 -0.0861 0.0445 0.6923 9.000 1.2442 0.03155 0.02246 -0.0845 0.0415 0.6960 9.250 1.2600 0.03246 0.02343 -0.0828 0.0391 0.6999 9.500 1.2756 0.03341 0.02444 -0.0812 0.0369 0.7046 9.750 1.2904 0.03444 0.02552 -0.0796 0.0353 0.7097 10.000 1.3050 0.03551 0.02666 -0.0779 0.0338 0.7150 10.250 1.3179 0.03663 0.02787 -0.0761 0.0326 0.7196 10.500 1.3297 0.03786 0.02918 -0.0742 0.0316 0.7244 10.750 1.3416 0.03911 0.03054 -0.0724 0.0306 0.7297 11.000 1.3528 0.04044 0.03196 -0.0707 0.0297 0.7353 11.250 1.3625 0.04186 0.03347 -0.0689 0.0290 0.7404 11.500 1.3703 0.04342 0.03512 -0.0669 0.0284 0.7460 11.750 1.3784 0.04503 0.03685 -0.0651 0.0277 0.7526 12.000 1.3862 0.04671 0.03866 -0.0634 0.0271 0.7596 12.250 1.3925 0.04845 0.04055 -0.0616 0.0265 0.7665 12.500 1.3978 0.05034 0.04256 -0.0599 0.0259 0.7745 12.750 1.4020 0.05236 0.04470 -0.0583 0.0255 0.7824 13.000 1.4045 0.05454 0.04699 -0.0567 0.0251 0.7910 13.500 1.4065 0.05944 0.05217 -0.0539 0.0243 0.8110 13.750 1.4068 0.06206 0.05498 -0.0527 0.0240 0.8232 14.250 1.4021 0.06780 0.06109 -0.0504 0.0233 0.8586 14.750 1.3837 0.07373 0.06739 -0.0472 0.0229 1.0001 15.000 1.3798 0.07779 0.07158 -0.0478 0.0227 1.0001 15.250 1.3747 0.08217 0.07610 -0.0488 0.0225 1.0001 15.500 1.3686 0.08688 0.08094 -0.0503 0.0223 1.0001 15.750 1.3610 0.09196 0.08615 -0.0521 0.0222 1.0001 16.000 1.3526 0.09737 0.09171 -0.0544 0.0220 1.0001 16.250 1.3432 0.10312 0.09760 -0.0572 0.0219 1.0001 16.500 1.3334 0.10915 0.10376 -0.0603 0.0218 1.0001 16.750 1.3228 0.11543 0.11018 -0.0638 0.0217 1.0001 17.000 1.3121 0.12187 0.11675 -0.0676 0.0216 1.0001 17.250 1.3012 0.12847 0.12348 -0.0717 0.0215 1.0001 17.500 1.2906 0.13513 0.13026 -0.0760 0.0214 1.0001 17.750 1.2804 0.14181 0.13705 -0.0804 0.0213 1.0001