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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.4131 0.05720 0.05478 -0.0822 0.9883 0.0064 -9.500 -0.4234 0.05211 0.04954 -0.0865 0.9828 0.0063 -9.250 -0.4371 0.04701 0.04425 -0.0883 0.9744 0.0063 -8.750 -0.4622 0.03772 0.03443 -0.0860 0.9483 0.0062 -8.500 -0.4655 0.03323 0.02955 -0.0841 0.9355 0.0063 -8.250 -0.4573 0.02978 0.02574 -0.0832 0.9249 0.0062 -8.000 -0.4380 0.02654 0.02209 -0.0838 0.9174 0.0063 -7.750 -0.4138 0.02402 0.01919 -0.0846 0.9081 0.0063 -7.500 -0.3796 0.02188 0.01665 -0.0870 0.9006 0.0065 -7.250 -0.3424 0.01959 0.01409 -0.0902 0.8907 0.0069 -7.000 -0.2971 0.01802 0.01227 -0.0944 0.8784 0.0070 -6.750 -0.2462 0.01664 0.01059 -0.0996 0.8625 0.0068 -6.500 -0.2076 0.01576 0.00949 -0.1022 0.8398 0.0067 -6.250 -0.1791 0.01513 0.00867 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3.500 0.8744 0.01060 0.00412 -0.1067 0.3990 0.8092 3.750 0.8993 0.01078 0.00431 -0.1062 0.3881 0.8111 4.000 0.9240 0.01099 0.00448 -0.1058 0.3761 0.8132 4.250 0.9489 0.01123 0.00467 -0.1054 0.3611 0.8155 4.500 0.9732 0.01155 0.00490 -0.1050 0.3391 0.8177 4.750 0.9970 0.01198 0.00517 -0.1047 0.3074 0.8200 5.000 1.0204 0.01251 0.00550 -0.1044 0.2712 0.8223 5.250 1.0400 0.01317 0.00593 -0.1033 0.2281 0.8239 5.500 1.0533 0.01412 0.00656 -0.1011 0.1686 0.8255 5.750 1.0677 0.01496 0.00717 -0.0991 0.1229 0.8272 6.000 1.0837 0.01562 0.00771 -0.0973 0.0928 0.8290 6.250 1.1024 0.01611 0.00815 -0.0959 0.0769 0.8310 6.500 1.1218 0.01662 0.00861 -0.0948 0.0610 0.8332 6.750 1.1435 0.01706 0.00904 -0.0941 0.0539 0.8355 7.000 1.1640 0.01765 0.00959 -0.0934 0.0359 0.8377 7.250 1.1837 0.01813 0.01007 -0.0924 0.0329 0.8392 7.500 1.2019 0.01860 0.01056 -0.0910 0.0299 0.8405 7.750 1.2206 0.01904 0.01106 -0.0898 0.0268 0.8418 8.000 1.2349 0.01972 0.01175 -0.0879 0.0163 0.8435 8.250 1.2491 0.02044 0.01246 -0.0861 0.0143 0.8454 8.500 1.2657 0.02105 0.01312 -0.0848 0.0130 0.8472 8.750 1.2828 0.02167 0.01380 -0.0836 0.0126 0.8490 9.000 1.2997 0.02233 0.01452 -0.0825 0.0122 0.8508 9.250 1.3161 0.02305 0.01531 -0.0814 0.0119 0.8525 9.500 1.3311 0.02385 0.01618 -0.0802 0.0116 0.8540 9.750 1.3433 0.02469 0.01711 -0.0785 0.0112 0.8552 10.000 1.3546 0.02564 0.01816 -0.0768 0.0109 0.8567 10.250 1.3650 0.02670 0.01931 -0.0752 0.0106 0.8583 10.500 1.3737 0.02798 0.02068 -0.0736 0.0100 0.8599 10.750 1.3818 0.02941 0.02220 -0.0722 0.0095 0.8614 11.000 1.3940 0.03056 0.02342 -0.0713 0.0093 0.8630 11.250 1.4058 0.03181 0.02475 -0.0706 0.0089 0.8645 11.500 1.4165 0.03323 0.02626 -0.0699 0.0083 0.8662 11.750 1.4266 0.03480 0.02791 -0.0693 0.0075 0.8678 12.000 1.4344 0.03648 0.02966 -0.0686 0.0067 0.8691 12.250 1.4433 0.03808 0.03137 -0.0679 0.0059 0.8703 12.500 1.4486 0.04010 0.03345 -0.0673 0.0031 0.8715 12.750 1.4510 0.04249 0.03590 -0.0667 0.0029 0.8727 13.000 1.4521 0.04508 0.03857 -0.0662 0.0027 0.8740 13.250 1.4527 0.04782 0.04142 -0.0659 0.0025 0.8755 13.500 1.4532 0.05067 0.04437 -0.0657 0.0024 0.8769 13.750 1.4533 0.05366 0.04745 -0.0656 0.0023 0.8782 14.000 1.4530 0.05676 0.05066 -0.0657 0.0022 0.8793 14.250 1.4519 0.06002 0.05402 -0.0659 0.0021 0.8804 14.500 1.4504 0.06338 0.05749 -0.0662 0.0021 0.8815 14.750 1.4486 0.06692 0.06114 -0.0667 0.0020 0.8824 15.000 1.4455 0.07048 0.06482 -0.0671 0.0020 0.8832 15.250 1.4414 0.07423 0.06869 -0.0675 0.0020 0.8841 15.500 1.4371 0.07804 0.07262 -0.0680 0.0019 0.8851 15.750 1.4325 0.08198 0.07669 -0.0687 0.0019 0.8860 16.000 1.4274 0.08603 0.08085 -0.0694 0.0019 0.8870 16.250 1.4216 0.09025 0.08520 -0.0703 0.0018 0.8880 16.500 1.4161 0.09450 0.08958 -0.0713 0.0018 0.8888 16.750 1.4100 0.09891 0.09410 -0.0724 0.0018 0.8897 17.000 1.4041 0.10338 0.09869 -0.0737 0.0017 0.8905 17.250 1.3978 0.10790 0.10333 -0.0751 0.0017 0.8913 17.500 1.3915 0.11251 0.10805 -0.0766 0.0017 0.8922 17.750 1.3852 0.11723 0.11289 -0.0784 0.0017 0.8930 18.000 1.3786 0.12204 0.11782 -0.0802 0.0017 0.8938 18.250 1.3719 0.12698 0.12288 -0.0823 0.0016 0.8945 18.500 1.3658 0.13173 0.12774 -0.0844 0.0016 0.8953 18.750 1.3589 0.13686 0.13298 -0.0868 0.0016 0.8961 19.000 1.3523 0.14190 0.13813 -0.0893 0.0016 0.8970