XFOIL Version 6.96 Calculated polar for: FX 63-147 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 ------ -------- --------- --------- -------- -------- -------- -10.000 -0.3892 0.05499 0.05317 -0.0950 0.9835 0.0037 -9.750 -0.4177 0.04833 0.04634 -0.0969 0.9758 0.0037 -9.500 -0.4453 0.04308 0.04089 -0.0951 0.9642 0.0037 -9.250 -0.4851 0.03387 0.03122 -0.0918 0.9462 0.0040 -9.000 -0.4862 0.02846 0.02533 -0.0911 0.9339 0.0042 -8.750 -0.4630 0.02562 0.02214 -0.0928 0.9238 0.0043 -8.500 -0.4249 0.02297 0.01900 -0.0973 0.9133 0.0046 -8.250 -0.3764 0.02025 0.01589 -0.1038 0.9003 0.0046 -8.000 -0.3338 0.01814 0.01341 -0.1084 0.8722 0.0047 -7.750 -0.3098 0.01710 0.01207 -0.1084 0.8357 0.0048 -7.500 -0.2899 0.01640 0.01112 -0.1073 0.8053 0.0048 -7.250 -0.2705 0.01559 0.01014 -0.1061 0.7826 0.0049 -7.000 -0.2499 0.01496 0.00936 -0.1051 0.7634 0.0050 -6.750 -0.2287 0.01443 0.00872 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3.500 0.9062 0.01051 0.00385 -0.1158 0.1845 0.7887 3.750 0.9239 0.01149 0.00444 -0.1144 0.1052 0.7911 4.000 0.9473 0.01196 0.00477 -0.1139 0.0784 0.7931 4.250 0.9711 0.01231 0.00506 -0.1133 0.0611 0.7949 4.500 0.9959 0.01257 0.00530 -0.1130 0.0536 0.7970 4.750 1.0186 0.01301 0.00566 -0.1123 0.0338 0.7994 5.000 1.0434 0.01329 0.00593 -0.1119 0.0292 0.8018 5.250 1.0689 0.01352 0.00617 -0.1117 0.0270 0.8039 5.500 1.0927 0.01387 0.00649 -0.1113 0.0165 0.8057 5.750 1.1167 0.01420 0.00680 -0.1109 0.0143 0.8074 6.000 1.1405 0.01448 0.00708 -0.1104 0.0130 0.8089 6.250 1.1637 0.01476 0.00739 -0.1097 0.0126 0.8105 6.500 1.1861 0.01507 0.00774 -0.1090 0.0120 0.8121 6.750 1.2066 0.01543 0.00813 -0.1079 0.0111 0.8139 7.000 1.2268 0.01580 0.00853 -0.1067 0.0103 0.8159 7.250 1.2476 0.01618 0.00894 -0.1058 0.0099 0.8180 7.500 1.2682 0.01658 0.00938 -0.1048 0.0095 0.8198 7.750 1.2893 0.01695 0.00976 -0.1039 0.0094 0.8214 8.000 1.3100 0.01734 0.01017 -0.1030 0.0092 0.8229 8.250 1.3290 0.01774 0.01061 -0.1018 0.0089 0.8243 8.500 1.3471 0.01816 0.01108 -0.1005 0.0085 0.8258 8.750 1.3649 0.01862 0.01157 -0.0991 0.0080 0.8273 9.000 1.3819 0.01911 0.01209 -0.0976 0.0075 0.8288 9.250 1.3975 0.01967 0.01268 -0.0960 0.0067 0.8303 9.500 1.4158 0.02014 0.01318 -0.0949 0.0059 0.8318 9.750 1.4288 0.02088 0.01391 -0.0931 0.0025 0.8334 10.000 1.4418 0.02167 0.01474 -0.0913 0.0020 0.8350 10.250 1.4547 0.02248 0.01561 -0.0896 0.0019 0.8365 10.500 1.4667 0.02339 0.01658 -0.0879 0.0017 0.8380 10.750 1.4776 0.02437 0.01763 -0.0861 0.0016 0.8394 11.000 1.4872 0.02545 0.01879 -0.0843 0.0016 0.8408 11.250 1.4964 0.02664 0.02005 -0.0826 0.0015 0.8421 11.500 1.5049 0.02793 0.02142 -0.0811 0.0014 0.8433 11.750 1.5124 0.02937 0.02294 -0.0796 0.0014 0.8447 12.000 1.5192 0.03097 0.02462 -0.0782 0.0013 0.8460 12.250 1.5253 0.03271 0.02645 -0.0771 0.0013 0.8475 12.500 1.5315 0.03454 0.02836 -0.0761 0.0013 0.8490 12.750 1.5367 0.03652 0.03043 -0.0753 0.0012 0.8504 13.000 1.5412 0.03867 0.03266 -0.0745 0.0012 0.8516 13.250 1.5449 0.04098 0.03506 -0.0740 0.0012 0.8527 13.500 1.5474 0.04345 0.03762 -0.0735 0.0012 0.8537 13.750 1.5487 0.04609 0.04035 -0.0730 0.0011 0.8549 14.000 1.5491 0.04890 0.04326 -0.0727 0.0011 0.8560 14.250 1.5487 0.05185 0.04632 -0.0725 0.0011 0.8570 14.500 1.5470 0.05499 0.04956 -0.0723 0.0011 0.8579 14.750 1.5449 0.05829 0.05296 -0.0723 0.0010 0.8588 15.000 1.5420 0.06170 0.05647 -0.0724 0.0010 0.8597 15.250 1.5382 0.06534 0.06022 -0.0726 0.0010 0.8606 15.500 1.5336 0.06907 0.06405 -0.0729 0.0010 0.8615 15.750 1.5288 0.07294 0.06803 -0.0734 0.0010 0.8624 16.000 1.5233 0.07696 0.07214 -0.0739 0.0010 0.8633 16.250 1.5169 0.08118 0.07647 -0.0746 0.0009 0.8642 16.500 1.5105 0.08541 0.08080 -0.0754 0.0009 0.8651 16.750 1.5034 0.08980 0.08529 -0.0763 0.0009 0.8659 17.000 1.4962 0.09431 0.08990 -0.0773 0.0009 0.8666 17.250 1.4888 0.09890 0.09459 -0.0785 0.0009 0.8672 17.500 1.4811 0.10356 0.09935 -0.0797 0.0009 0.8678 17.750 1.4732 0.10832 0.10421 -0.0812 0.0009 0.8683 18.000 1.4648 0.11318 0.10918 -0.0827 0.0008 0.8689 18.250 1.4560 0.11822 0.11432 -0.0845 0.0008 0.8696 18.500 1.4478 0.12310 0.11930 -0.0862 0.0008 0.8703 18.750 1.4389 0.12831 0.12462 -0.0883 0.0008 0.8709