XFOIL Version 6.96 Calculated polar for: GOE 457 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.000 -0.3845 0.09137 0.08925 -0.0222 1.0000 0.0210 -7.750 -0.3986 0.08989 0.08782 -0.0194 1.0000 0.0210 -7.500 -0.4079 0.08771 0.08568 -0.0182 1.0000 0.0210 -7.250 -0.4019 0.08366 0.08164 -0.0216 0.9990 0.0210 -7.000 -0.3886 0.07790 0.07589 -0.0253 0.9965 0.0216 -6.750 -0.3644 0.07417 0.07214 -0.0301 0.9943 0.0220 -6.500 -0.3419 0.07051 0.06846 -0.0348 0.9909 0.0227 -6.250 -0.3142 0.06596 0.06387 -0.0419 0.9874 0.0238 -6.000 -0.2641 0.05776 0.05551 -0.0582 0.9843 0.0268 -5.750 -0.2322 0.05125 0.04885 -0.0657 0.9795 0.0270 -5.500 -0.2093 0.04337 0.04081 -0.0724 0.9753 0.0281 -5.250 -0.1770 0.04113 0.03852 -0.0758 0.9731 0.0291 -5.000 -0.1392 0.03738 0.03461 -0.0808 0.9714 0.0312 -4.750 -0.1063 0.03305 0.02976 -0.0828 0.9651 0.0350 -4.500 -0.0814 0.02693 0.02341 -0.0861 0.9618 0.0372 -4.250 -0.0465 0.02585 0.02227 -0.0884 0.9599 0.0402 -4.000 -0.0101 0.01853 0.01380 -0.0902 0.9581 0.0357 -3.750 0.0127 0.01621 0.01117 -0.0893 0.9520 0.0363 -3.500 0.0472 0.01443 0.00912 -0.0905 0.9490 0.0365 -3.250 0.0843 0.01306 0.00758 -0.0923 0.9466 0.0374 -3.000 0.1222 0.01226 0.00671 -0.0943 0.9441 0.0392 -2.750 0.1484 0.01151 0.00587 -0.0936 0.9366 0.0399 -2.500 0.1832 0.01071 0.00499 -0.0947 0.9315 0.0406 -2.250 0.2129 0.01012 0.00433 -0.0947 0.9236 0.0414 -2.000 0.2465 0.00961 0.00378 -0.0956 0.9156 0.0430 -1.750 0.2742 0.00921 0.00333 -0.0951 0.9038 0.0440 -1.500 0.3026 0.00887 0.00293 -0.0949 0.8904 0.0447 -1.250 0.3300 0.00849 0.00249 -0.0944 0.8739 0.0459 -1.000 0.3564 0.00820 0.00214 -0.0937 0.8514 0.0482 -0.750 0.3824 0.00805 0.00189 -0.0929 0.8134 0.0515 -0.500 0.4058 0.00814 0.00166 -0.0914 0.7422 0.0560 -0.250 0.4265 0.00832 0.00159 -0.0896 0.6794 0.0731 0.000 0.4477 0.00837 0.00156 -0.0881 0.6263 0.1275 0.250 0.4689 0.00825 0.00164 -0.0868 0.5869 0.2680 0.500 0.4904 0.00801 0.00173 -0.0856 0.5606 0.4411 0.750 0.5430 0.00694 0.00187 -0.0912 0.5377 1.0000 1.000 0.5673 0.00711 0.00192 -0.0903 0.5226 1.0000 1.250 0.5919 0.00728 0.00197 -0.0895 0.5092 1.0000 1.500 0.6167 0.00745 0.00204 -0.0887 0.4967 1.0000 1.750 0.6415 0.00762 0.00211 -0.0879 0.4851 1.0000 2.000 0.6669 0.00775 0.00218 -0.0873 0.4734 1.0000 2.250 0.6920 0.00789 0.00225 -0.0866 0.4608 1.0000 2.500 0.7172 0.00804 0.00233 -0.0859 0.4488 1.0000 2.750 0.7422 0.00819 0.00243 -0.0852 0.4370 1.0000 3.000 0.7672 0.00835 0.00251 -0.0845 0.4222 1.0000 3.250 0.7922 0.00851 0.00260 -0.0839 0.4061 1.0000 3.500 0.8172 0.00867 0.00271 -0.0832 0.3929 1.0000 3.750 0.8422 0.00884 0.00283 -0.0825 0.3810 1.0000 4.000 0.8673 0.00901 0.00296 -0.0819 0.3677 1.0000 4.250 0.8922 0.00920 0.00309 -0.0813 0.3536 1.0000 4.500 0.9169 0.00940 0.00325 -0.0806 0.3391 1.0000 4.750 0.9418 0.00960 0.00342 -0.0800 0.3260 1.0000 5.000 0.9665 0.00981 0.00359 -0.0793 0.3135 1.0000 5.250 0.9911 0.01004 0.00378 -0.0787 0.3005 1.0000 5.500 1.0155 0.01028 0.00400 -0.0780 0.2861 1.0000 5.750 1.0394 0.01056 0.00422 -0.0772 0.2675 1.0000 6.000 1.0627 0.01091 0.00446 -0.0764 0.2437 1.0000 6.250 1.0854 0.01132 0.00475 -0.0755 0.2162 1.0000 6.500 1.1064 0.01191 0.00513 -0.0744 0.1739 1.0000 6.750 1.1252 0.01274 0.00567 -0.0730 0.1270 1.0000 7.000 1.1462 0.01333 0.00617 -0.0719 0.1093 1.0000 7.500 1.1902 0.01425 0.00704 -0.0700 0.0897 1.0000 7.750 1.2122 0.01467 0.00746 -0.0690 0.0823 1.0000 8.000 1.2344 0.01507 0.00785 -0.0681 0.0756 1.0000 8.250 1.2566 0.01545 0.00823 -0.0672 0.0688 1.0000 8.500 1.2778 0.01592 0.00865 -0.0662 0.0592 1.0000 8.750 1.2983 0.01643 0.00910 -0.0650 0.0474 1.0000 9.250 1.3287 0.01834 0.01084 -0.0611 0.0177 1.0000 9.500 1.3451 0.01913 0.01172 -0.0592 0.0161 1.0000 9.750 1.3606 0.01995 0.01267 -0.0572 0.0150 1.0000 10.000 1.3760 0.02071 0.01355 -0.0553 0.0143 1.0000 10.250 1.3893 0.02155 0.01449 -0.0530 0.0137 1.0000 10.500 1.3983 0.02249 0.01554 -0.0500 0.0131 1.0000 10.750 1.4052 0.02351 0.01666 -0.0469 0.0127 1.0000 11.000 1.4098 0.02467 0.01791 -0.0435 0.0124 1.0000 11.250 1.4113 0.02603 0.01939 -0.0400 0.0121 1.0000 11.500 1.4098 0.02764 0.02111 -0.0364 0.0118 1.0000 11.750 1.4038 0.02965 0.02324 -0.0328 0.0115 1.0000 12.000 1.3950 0.03207 0.02578 -0.0294 0.0113 1.0000 12.250 1.3934 0.03413 0.02795 -0.0271 0.0112 1.0000 12.500 1.3949 0.03605 0.02999 -0.0254 0.0110 1.0000 12.750 1.3952 0.03822 0.03227 -0.0239 0.0109 1.0000 13.000 1.3988 0.04020 0.03438 -0.0231 0.0106 1.0000 13.250 1.3963 0.04300 0.03731 -0.0224 0.0104 1.0000 13.500 1.3937 0.04602 0.04045 -0.0221 0.0103 1.0000 13.750 1.3907 0.04931 0.04386 -0.0222 0.0100 1.0000 14.000 1.3866 0.05290 0.04758 -0.0227 0.0099 1.0000 14.250 1.3821 0.05670 0.05151 -0.0234 0.0098 1.0000 14.500 1.3777 0.06063 0.05555 -0.0244 0.0096 1.0000 14.750 1.3727 0.06472 0.05975 -0.0255 0.0095 1.0000 15.000 1.3671 0.06898 0.06413 -0.0267 0.0094 1.0000 15.250 1.3616 0.07331 0.06858 -0.0280 0.0093 1.0000 15.500 1.3554 0.07784 0.07323 -0.0295 0.0093 1.0000 15.750 1.3488 0.08251 0.07800 -0.0313 0.0091 1.0000 16.000 1.3421 0.08734 0.08295 -0.0331 0.0091 1.0000 16.250 1.3349 0.09233 0.08807 -0.0351 0.0091 1.0000 16.500 1.3273 0.09755 0.09341 -0.0374 0.0091 1.0000 16.750 1.3194 0.10297 0.09895 -0.0399 0.0090 1.0000 17.000 1.3114 0.10852 0.10462 -0.0426 0.0089 1.0000 17.250 1.3027 0.11434 0.11056 -0.0456 0.0089 1.0000 17.500 1.2933 0.12051 0.11687 -0.0488 0.0089 1.0000 17.750 1.2840 0.12684 0.12334 -0.0524 0.0089 1.0000 18.000 1.2740 0.13341 0.13005 -0.0562 0.0089 1.0000 18.250 1.2634 0.14033 0.13711 -0.0603 0.0089 1.0000 18.500 1.2526 0.14749 0.14440 -0.0647 0.0089 1.0000 18.750 1.2406 0.15520 0.15225 -0.0696 0.0090 1.0000 19.000 1.2158 0.16707 0.16437 -0.0774 0.0093 1.0000