XFOIL Version 6.96 Calculated polar for: GOE 416A 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 ------ -------- --------- --------- -------- -------- -------- -11.500 -0.6224 0.10961 0.10804 0.0035 1.0000 0.0028 -11.250 -0.6282 0.10295 0.10139 0.0002 1.0000 0.0028 -11.000 -0.6360 0.09515 0.09361 -0.0040 1.0000 0.0028 -10.750 -0.6532 0.08260 0.08103 -0.0123 1.0000 0.0027 -10.500 -0.6722 0.07349 0.07183 -0.0197 1.0000 0.0027 -10.250 -0.6898 0.06617 0.06441 -0.0260 1.0000 0.0026 -10.000 -0.7059 0.05990 0.05803 -0.0319 1.0000 0.0026 -9.750 -0.7217 0.05458 0.05259 -0.0372 1.0000 0.0026 -9.500 -0.7325 0.05031 0.04814 -0.0394 1.0000 0.0026 -9.250 -0.7358 0.04589 0.04350 -0.0405 1.0000 0.0026 -9.000 -0.7341 0.04146 0.03882 -0.0408 1.0000 0.0026 -8.750 -0.7285 0.03698 0.03404 -0.0406 1.0000 0.0026 -8.500 -0.7203 0.03201 0.02870 -0.0399 1.0000 0.0026 -8.250 -0.7099 0.02614 0.02235 -0.0383 1.0000 0.0028 -8.000 -0.6892 0.02182 0.01761 -0.0385 0.9947 0.0030 -7.750 -0.6607 0.02027 0.01588 -0.0396 0.9871 0.0031 -7.500 -0.6318 0.01914 0.01463 -0.0405 0.9784 0.0032 -7.250 -0.6041 0.01783 0.01319 -0.0410 0.9687 0.0033 -7.000 -0.5778 0.01655 0.01175 -0.0411 0.9574 0.0035 -6.750 -0.5530 0.01542 0.01050 -0.0407 0.9446 0.0036 -6.500 -0.5285 0.01457 0.00954 -0.0402 0.9323 0.0039 -6.250 -0.5043 0.01361 0.00846 -0.0397 0.9210 0.0041 -6.000 -0.4801 0.01269 0.00740 -0.0392 0.9093 0.0043 -5.750 -0.4548 0.01198 0.00657 -0.0388 0.8966 0.0045 -5.500 -0.4289 0.01137 0.00586 -0.0386 0.8838 0.0047 -5.250 -0.4029 0.01070 0.00508 -0.0385 0.8714 0.0050 -5.000 -0.3757 0.01038 0.00468 -0.0385 0.8582 0.0053 -4.750 -0.3484 0.01008 0.00431 -0.0385 0.8432 0.0057 -4.500 -0.3211 0.00979 0.00391 -0.0385 0.8253 0.0061 -4.250 -0.2935 0.00953 0.00354 -0.0385 0.8051 0.0066 -4.000 -0.2658 0.00942 0.00331 -0.0385 0.7796 0.0071 -3.750 -0.2384 0.00911 0.00283 -0.0385 0.7467 0.0080 -3.500 -0.2105 0.00899 0.00259 -0.0385 0.7155 0.0087 -3.250 -0.1823 0.00889 0.00236 -0.0387 0.6900 0.0097 -3.000 -0.1539 0.00881 0.00218 -0.0388 0.6710 0.0107 -2.750 -0.1254 0.00867 0.00193 -0.0390 0.6544 0.0128 -2.500 -0.0968 0.00858 0.00177 -0.0392 0.6389 0.0155 -2.250 -0.0682 0.00853 0.00163 -0.0394 0.6238 0.0188 -2.000 -0.0406 0.00753 0.00123 -0.0400 0.6090 0.2293 -1.750 -0.0132 0.00670 0.00098 -0.0406 0.5952 0.4039 -1.500 0.0155 0.00665 0.00100 -0.0409 0.5838 0.4478 -1.250 0.0444 0.00668 0.00099 -0.0411 0.5723 0.4583 -1.000 0.0733 0.00671 0.00101 -0.0413 0.5593 0.4697 -0.750 0.1021 0.00677 0.00101 -0.0415 0.5427 0.4776 -0.500 0.1308 0.00684 0.00101 -0.0417 0.5215 0.4811 -0.250 0.1595 0.00693 0.00101 -0.0419 0.5002 0.4843 0.000 0.1881 0.00704 0.00102 -0.0421 0.4773 0.4871 0.250 0.2166 0.00715 0.00104 -0.0422 0.4570 0.4896 0.500 0.2451 0.00723 0.00108 -0.0424 0.4398 0.4923 0.750 0.2738 0.00731 0.00112 -0.0426 0.4281 0.4947 1.000 0.3024 0.00739 0.00116 -0.0428 0.4160 0.4967 1.250 0.3310 0.00749 0.00121 -0.0430 0.4020 0.4986 1.500 0.3596 0.00757 0.00126 -0.0432 0.3908 0.5002 1.750 0.3883 0.00765 0.00131 -0.0434 0.3811 0.5019 2.000 0.4169 0.00773 0.00137 -0.0436 0.3699 0.5038 2.250 0.4454 0.00781 0.00144 -0.0438 0.3591 0.5058 2.500 0.4739 0.00789 0.00151 -0.0439 0.3462 0.5078 2.750 0.5022 0.00801 0.00159 -0.0441 0.3281 0.5097 3.000 0.5296 0.00828 0.00172 -0.0442 0.2848 0.5117 3.250 0.5563 0.00868 0.00192 -0.0442 0.2382 0.5138 3.500 0.5839 0.00893 0.00209 -0.0443 0.2182 0.5161 4.000 0.6399 0.00922 0.00237 -0.0445 0.2003 0.5206 4.250 0.6681 0.00933 0.00252 -0.0447 0.1936 0.5230 4.500 0.6959 0.00948 0.00268 -0.0447 0.1850 0.5255 4.750 0.7238 0.00963 0.00284 -0.0448 0.1748 0.5282 5.000 0.7506 0.00996 0.00305 -0.0448 0.1426 0.5307 5.250 0.7760 0.01051 0.00341 -0.0447 0.1009 0.5333 5.500 0.8024 0.01088 0.00371 -0.0446 0.0793 0.5366 5.750 0.8280 0.01135 0.00406 -0.0445 0.0536 0.5402 6.000 0.8546 0.01167 0.00437 -0.0444 0.0432 0.5439 6.500 0.9069 0.01238 0.00506 -0.0442 0.0237 0.5512 6.750 0.9319 0.01290 0.00552 -0.0439 0.0112 0.5555 7.000 0.9577 0.01329 0.00594 -0.0437 0.0082 0.5601 7.250 0.9836 0.01363 0.00635 -0.0435 0.0070 0.5650 7.500 1.0088 0.01406 0.00683 -0.0433 0.0060 0.5708 7.750 1.0340 0.01448 0.00732 -0.0430 0.0052 0.5768 8.000 1.0593 0.01486 0.00780 -0.0428 0.0047 0.5843 8.250 1.0840 0.01528 0.00829 -0.0425 0.0042 0.5929 8.500 1.1081 0.01579 0.00887 -0.0421 0.0038 0.6038 8.750 1.1313 0.01639 0.00959 -0.0415 0.0035 0.6168 9.000 1.1551 0.01686 0.01018 -0.0411 0.0033 0.6336 9.250 1.1783 0.01737 0.01083 -0.0406 0.0031 0.6574 9.500 1.2009 0.01788 0.01152 -0.0401 0.0029 0.6996 9.750 1.2186 0.01786 0.01219 -0.0384 0.0028 1.0000 10.000 1.2402 0.01854 0.01293 -0.0377 0.0026 1.0000 10.250 1.2612 0.01925 0.01372 -0.0370 0.0025 1.0000 10.500 1.2810 0.02005 0.01460 -0.0361 0.0024 1.0000 10.750 1.2980 0.02109 0.01574 -0.0349 0.0022 1.0000 11.000 1.3143 0.02213 0.01688 -0.0337 0.0021 1.0000 11.250 1.3321 0.02295 0.01778 -0.0326 0.0020 1.0000 11.500 1.3482 0.02386 0.01879 -0.0313 0.0020 1.0000 11.750 1.3626 0.02484 0.01987 -0.0299 0.0019 1.0000 12.000 1.3731 0.02591 0.02105 -0.0280 0.0018 1.0000 12.250 1.3799 0.02709 0.02234 -0.0256 0.0018 1.0000 12.500 1.3850 0.02847 0.02384 -0.0234 0.0017 1.0000 12.750 1.3894 0.03003 0.02551 -0.0216 0.0017 1.0000 13.000 1.3923 0.03185 0.02745 -0.0201 0.0016 1.0000 13.250 1.3943 0.03391 0.02964 -0.0191 0.0016 1.0000 13.500 1.3951 0.03629 0.03215 -0.0185 0.0016 1.0000 13.750 1.3943 0.03906 0.03504 -0.0183 0.0015 1.0000 14.000 1.3920 0.04227 0.03839 -0.0187 0.0015 1.0000 14.250 1.3887 0.04585 0.04210 -0.0197 0.0015 1.0000 14.500 1.3823 0.05011 0.04650 -0.0212 0.0015 1.0000 14.750 1.3741 0.05479 0.05132 -0.0230 0.0014 1.0000 15.000 1.3618 0.06027 0.05695 -0.0254 0.0014 1.0000 15.250 1.3488 0.06607 0.06288 -0.0280 0.0014 1.0000 15.500 1.3315 0.07277 0.06972 -0.0311 0.0014 1.0000 15.750 1.3117 0.08003 0.07713 -0.0346 0.0014 1.0000 16.000 1.2898 0.08783 0.08507 -0.0383 0.0014 1.0000 16.250 1.2661 0.09629 0.09367 -0.0423 0.0014 1.0000 16.500 1.2408 0.10531 0.10283 -0.0467 0.0014 1.0000 16.750 1.2158 0.11465 0.11230 -0.0512 0.0015 1.0000