XFOIL Version 6.96 Calculated polar for: GOE 411 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 ------ -------- --------- --------- -------- -------- -------- -14.250 -0.7132 0.09547 0.09361 -0.0331 1.0000 0.0017 -14.000 -0.7270 0.08845 0.08653 -0.0374 1.0000 0.0017 -13.750 -0.7487 0.08037 0.07833 -0.0422 1.0000 0.0017 -13.500 -0.7707 0.07305 0.07087 -0.0465 1.0000 0.0017 -13.250 -0.7916 0.06663 0.06432 -0.0498 1.0000 0.0017 -13.000 -0.8196 0.05973 0.05723 -0.0526 1.0000 0.0017 -12.750 -0.8278 0.05643 0.05385 -0.0537 1.0000 0.0016 -12.500 -0.8546 0.05094 0.04815 -0.0540 1.0000 0.0017 -12.250 -0.8752 0.04684 0.04386 -0.0529 1.0000 0.0017 -12.000 -0.9034 0.04165 0.03839 -0.0500 1.0000 0.0018 -11.750 -0.9122 0.03977 0.03639 -0.0476 1.0000 0.0016 -11.500 -0.9361 0.03502 0.03130 -0.0427 1.0000 0.0018 -11.250 -0.9605 0.02914 0.02495 -0.0367 1.0000 0.0020 -11.000 -0.9580 0.02797 0.02365 -0.0335 1.0000 0.0021 -10.750 -0.9616 0.02633 0.02185 -0.0292 1.0000 0.0021 -10.500 -0.9654 0.02484 0.02021 -0.0245 1.0000 0.0021 -10.250 -0.9682 0.02376 0.01900 -0.0197 1.0000 0.0022 -10.000 -0.9598 0.02269 0.01783 -0.0172 0.9993 0.0023 -9.750 -0.9458 0.02094 0.01589 -0.0159 0.9974 0.0023 -9.500 -0.9243 0.02019 0.01507 -0.0157 0.9956 0.0024 -9.250 -0.9032 0.01954 0.01436 -0.0152 0.9936 0.0024 -9.000 -0.8831 0.01873 0.01347 -0.0145 0.9912 0.0025 -8.750 -0.8591 0.01789 0.01256 -0.0145 0.9890 0.0026 -8.500 -0.8332 0.01693 0.01152 -0.0150 0.9872 0.0027 -8.250 -0.8053 0.01661 0.01118 -0.0156 0.9845 0.0030 -8.000 -0.7837 0.01561 0.01007 -0.0150 0.9808 0.0031 -7.750 -0.7575 0.01482 0.00920 -0.0153 0.9787 0.0033 -7.500 -0.7337 0.01423 0.00852 -0.0150 0.9755 0.0034 -7.250 -0.7098 0.01361 0.00783 -0.0146 0.9717 0.0036 -7.000 -0.6842 0.01284 0.00699 -0.0146 0.9693 0.0040 -6.750 -0.6596 0.01236 0.00646 -0.0143 0.9654 0.0042 -6.500 -0.6318 0.01201 0.00610 -0.0147 0.9613 0.0046 -6.250 -0.5997 0.01160 0.00566 -0.0160 0.9589 0.0051 -6.000 -0.5724 0.01122 0.00523 -0.0161 0.9532 0.0054 -5.750 -0.5405 0.01079 0.00475 -0.0174 0.9487 0.0061 -5.500 -0.5117 0.01044 0.00438 -0.0179 0.9425 0.0071 -5.250 -0.4795 0.01012 0.00402 -0.0191 0.9366 0.0078 -5.000 -0.4502 0.00987 0.00373 -0.0197 0.9285 0.0087 -4.750 -0.4196 0.00959 0.00339 -0.0205 0.9201 0.0103 -4.500 -0.3897 0.00935 0.00310 -0.0211 0.9094 0.0137 -4.250 -0.3616 0.00918 0.00287 -0.0214 0.8960 0.0164 -4.000 -0.3393 0.00873 0.00252 -0.0204 0.8809 0.0700 -3.750 -0.3215 0.00814 0.00219 -0.0187 0.8637 0.1464 -3.500 -0.2989 0.00792 0.00202 -0.0177 0.8481 0.1726 -3.250 -0.2780 0.00766 0.00185 -0.0165 0.8323 0.2098 -3.000 -0.2595 0.00728 0.00166 -0.0147 0.8167 0.2688 -2.750 -0.2411 0.00694 0.00150 -0.0130 0.8008 0.3294 -2.500 -0.2198 0.00678 0.00141 -0.0117 0.7846 0.3645 -2.000 -0.1756 0.00668 0.00127 -0.0094 0.7402 0.4005 -1.750 -0.1556 0.00671 0.00121 -0.0077 0.7016 0.4173 -1.500 -0.1351 0.00679 0.00117 -0.0062 0.6647 0.4299 -1.250 -0.1141 0.00685 0.00115 -0.0048 0.6322 0.4439 -1.000 -0.0912 0.00688 0.00113 -0.0039 0.6102 0.4576 -0.500 -0.0447 0.00694 0.00111 -0.0021 0.5697 0.4830 -0.250 -0.0220 0.00694 0.00110 -0.0011 0.5487 0.5023 0.000 -0.0001 0.00695 0.00110 0.0000 0.5233 0.5245 0.250 0.0218 0.00695 0.00111 0.0012 0.5009 0.5485 0.500 0.0447 0.00693 0.00111 0.0021 0.4836 0.5705 0.750 0.0683 0.00692 0.00112 0.0029 0.4702 0.5886 1.000 0.0912 0.00689 0.00113 0.0039 0.4567 0.6093 1.250 0.1140 0.00685 0.00115 0.0049 0.4438 0.6327 1.500 0.1351 0.00678 0.00117 0.0062 0.4302 0.6652 1.750 0.1550 0.00671 0.00121 0.0079 0.4154 0.7052 2.000 0.1757 0.00668 0.00127 0.0093 0.4008 0.7395 2.500 0.2199 0.00677 0.00141 0.0117 0.3650 0.7846 2.750 0.2402 0.00699 0.00151 0.0131 0.3210 0.8008 3.000 0.2592 0.00731 0.00167 0.0148 0.2646 0.8163 3.250 0.2777 0.00769 0.00185 0.0165 0.2059 0.8319 3.500 0.2990 0.00792 0.00201 0.0177 0.1729 0.8479 3.750 0.3215 0.00814 0.00219 0.0187 0.1462 0.8638 4.250 0.3615 0.00918 0.00287 0.0214 0.0163 0.8958 4.500 0.3897 0.00935 0.00310 0.0211 0.0135 0.9093 4.750 0.4195 0.00960 0.00340 0.0205 0.0105 0.9200 5.000 0.4506 0.00987 0.00373 0.0196 0.0088 0.9291 5.250 0.4797 0.01012 0.00401 0.0191 0.0076 0.9367 5.500 0.5117 0.01043 0.00436 0.0179 0.0070 0.9422 5.750 0.5399 0.01086 0.00483 0.0175 0.0058 0.9487 6.000 0.5729 0.01119 0.00520 0.0160 0.0053 0.9532 6.250 0.5999 0.01157 0.00562 0.0159 0.0049 0.9589 6.500 0.6325 0.01197 0.00604 0.0145 0.0045 0.9613 6.750 0.6590 0.01243 0.00655 0.0145 0.0043 0.9656 7.000 0.6847 0.01283 0.00698 0.0145 0.0040 0.9694 7.250 0.7103 0.01359 0.00781 0.0145 0.0037 0.9718 7.500 0.7319 0.01434 0.00865 0.0153 0.0036 0.9758 7.750 0.7566 0.01493 0.00933 0.0154 0.0034 0.9788 8.000 0.7848 0.01551 0.00996 0.0148 0.0031 0.9808 8.250 0.8059 0.01656 0.01112 0.0155 0.0030 0.9845 8.500 0.8315 0.01718 0.01180 0.0153 0.0028 0.9873 8.750 0.8607 0.01775 0.01240 0.0142 0.0026 0.9889 9.000 0.8819 0.01889 0.01365 0.0146 0.0026 0.9913 9.250 0.9049 0.01941 0.01422 0.0149 0.0024 0.9935 9.500 0.9239 0.02029 0.01518 0.0157 0.0024 0.9956 9.750 0.9467 0.02091 0.01585 0.0157 0.0023 0.9974 10.000 0.9611 0.02259 0.01772 0.0170 0.0023 0.9993 10.250 0.9650 0.02406 0.01933 0.0202 0.0021 1.0000 10.500 0.9618 0.02526 0.02066 0.0251 0.0021 1.0000 10.750 0.9650 0.02599 0.02148 0.0287 0.0020 1.0000 11.000 0.9635 0.02742 0.02306 0.0328 0.0020 1.0000 11.250 0.9554 0.02982 0.02568 0.0373 0.0020 1.0000 11.500 0.9486 0.03245 0.02854 0.0412 0.0019 1.0000 11.750 0.9113 0.03987 0.03650 0.0476 0.0017 1.0000 12.000 0.9072 0.04115 0.03786 0.0497 0.0018 1.0000 12.250 0.8724 0.04727 0.04431 0.0530 0.0017 1.0000 12.500 0.8568 0.05078 0.04797 0.0539 0.0017 1.0000 12.750 0.8360 0.05536 0.05273 0.0537 0.0017 1.0000 13.000 0.8170 0.06031 0.05783 0.0524 0.0016 1.0000 13.250 0.7972 0.06592 0.06358 0.0500 0.0017 1.0000 13.500 0.7775 0.07209 0.06989 0.0468 0.0017 1.0000 13.750 0.7488 0.08067 0.07863 0.0419 0.0016 1.0000 14.000 0.7399 0.08597 0.08399 0.0385 0.0017 1.0000 14.250 0.7101 0.09664 0.09480 0.0322 0.0017 1.0000 14.500 0.6953 0.10449 0.10273 0.0275 0.0018 1.0000 14.750 0.6799 0.11305 0.11133 0.0227 0.0018 1.0000 15.000 0.6637 0.12229 0.12062 0.0181 0.0019 1.0000