XFOIL Version 6.96 Calculated polar for: GOE 491 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 ------ -------- --------- --------- -------- -------- -------- -8.000 -0.4703 0.08835 0.08677 -0.0061 1.0000 0.0028 -7.750 -0.4707 0.08586 0.08429 -0.0066 1.0000 0.0027 -7.500 -0.4748 0.08180 0.08027 -0.0081 1.0000 0.0028 -7.250 -0.4686 0.07907 0.07754 -0.0099 1.0000 0.0026 -7.000 -0.4648 0.07433 0.07280 -0.0128 1.0000 0.0027 -6.750 -0.4579 0.06993 0.06839 -0.0154 1.0000 0.0028 -6.500 -0.4494 0.06534 0.06378 -0.0179 1.0000 0.0028 -6.000 -0.4114 0.05562 0.05394 -0.0260 0.9981 0.0032 -5.500 -0.3735 0.01680 0.01331 -0.0383 0.9839 0.0033 -5.000 -0.3222 0.01332 0.00929 -0.0378 0.9728 0.0036 -4.750 -0.2952 0.01187 0.00754 -0.0377 0.9652 0.0037 -4.500 -0.2649 0.01084 0.00630 -0.0382 0.9562 0.0040 -4.250 -0.2281 0.00993 0.00519 -0.0401 0.9474 0.0044 -4.000 -0.1854 0.00928 0.00437 -0.0434 0.9374 0.0048 -3.750 -0.1429 0.00851 0.00339 -0.0467 0.9192 0.0053 -3.500 -0.1105 0.00814 0.00289 -0.0476 0.8967 0.0060 -3.250 -0.0836 0.00795 0.00259 -0.0473 0.8764 0.0067 -3.000 -0.0579 0.00778 0.00231 -0.0467 0.8580 0.0076 -2.750 -0.0329 0.00753 0.00192 -0.0459 0.8375 0.0087 -2.500 -0.0083 0.00733 0.00161 -0.0450 0.8144 0.0108 -2.250 0.0158 0.00725 0.00138 -0.0440 0.7819 0.0131 -2.000 0.0395 0.00719 0.00120 -0.0429 0.7463 0.0236 -1.750 0.0633 0.00721 0.00114 -0.0420 0.7087 0.0363 -1.500 0.0880 0.00729 0.00111 -0.0412 0.6742 0.0420 -1.250 0.1128 0.00736 0.00103 -0.0405 0.6392 0.0445 -1.000 0.1377 0.00742 0.00101 -0.0398 0.6046 0.0505 -0.750 0.1625 0.00751 0.00095 -0.0391 0.5647 0.0526 -0.500 0.1869 0.00765 0.00088 -0.0383 0.5144 0.0538 -0.250 0.2099 0.00795 0.00087 -0.0374 0.4373 0.0548 0.000 0.2353 0.00804 0.00084 -0.0368 0.4112 0.0557 0.250 0.2612 0.00804 0.00079 -0.0364 0.3971 0.0597 0.500 0.2873 0.00806 0.00078 -0.0360 0.3830 0.0639 0.750 0.3134 0.00810 0.00077 -0.0356 0.3685 0.0676 1.000 0.3395 0.00813 0.00077 -0.0352 0.3537 0.0750 1.500 0.3915 0.00819 0.00081 -0.0344 0.3235 0.0987 1.750 0.4164 0.00824 0.00085 -0.0338 0.2961 0.1400 2.000 0.4400 0.00819 0.00095 -0.0330 0.2642 0.2559 2.500 0.5410 0.00739 0.00148 -0.0444 0.1480 0.9937 2.750 0.5823 0.00788 0.00167 -0.0478 0.0855 0.9981 3.000 0.6169 0.00831 0.00189 -0.0496 0.0378 1.0000 3.250 0.6410 0.00848 0.00204 -0.0488 0.0350 1.0000 3.500 0.6653 0.00863 0.00218 -0.0480 0.0339 1.0000 3.750 0.6895 0.00878 0.00234 -0.0472 0.0331 1.0000 4.000 0.7136 0.00895 0.00252 -0.0464 0.0320 1.0000 4.250 0.7376 0.00913 0.00273 -0.0456 0.0315 1.0000 4.500 0.7616 0.00931 0.00295 -0.0448 0.0312 1.0000 4.750 0.7855 0.00952 0.00318 -0.0440 0.0309 1.0000 5.000 0.8090 0.00976 0.00346 -0.0431 0.0299 1.0000 5.250 0.8327 0.00996 0.00370 -0.0423 0.0289 1.0000 5.500 0.8569 0.01010 0.00385 -0.0416 0.0283 1.0000 5.750 0.8810 0.01026 0.00403 -0.0409 0.0272 1.0000 6.000 0.9050 0.01043 0.00423 -0.0401 0.0246 1.0000 6.250 0.9281 0.01069 0.00447 -0.0393 0.0183 1.0000 6.500 0.9506 0.01105 0.00479 -0.0383 0.0113 1.0000 6.750 0.9728 0.01144 0.00517 -0.0373 0.0079 1.0000 7.000 0.9948 0.01184 0.00561 -0.0362 0.0061 1.0000 7.250 1.0167 0.01225 0.00605 -0.0351 0.0051 1.0000 7.500 1.0377 0.01277 0.00663 -0.0339 0.0043 1.0000 7.750 1.0595 0.01320 0.00712 -0.0328 0.0039 1.0000 8.000 1.0808 0.01366 0.00766 -0.0317 0.0035 1.0000 8.250 1.1016 0.01418 0.00828 -0.0304 0.0033 1.0000 8.500 1.1218 0.01475 0.00891 -0.0292 0.0029 1.0000 8.750 1.1401 0.01556 0.00982 -0.0276 0.0027 1.0000 9.000 1.1594 0.01621 0.01057 -0.0262 0.0025 1.0000 9.250 1.1786 0.01687 0.01133 -0.0248 0.0024 1.0000 9.500 1.1978 0.01750 0.01204 -0.0235 0.0022 1.0000 9.750 1.2160 0.01822 0.01286 -0.0220 0.0020 1.0000 10.000 1.2333 0.01903 0.01378 -0.0205 0.0019 1.0000 10.250 1.2506 0.01981 0.01465 -0.0189 0.0018 1.0000 10.500 1.2673 0.02063 0.01557 -0.0174 0.0017 1.0000 10.750 1.2812 0.02170 0.01677 -0.0154 0.0017 1.0000 11.000 1.2922 0.02301 0.01823 -0.0132 0.0015 1.0000 11.250 1.2978 0.02479 0.02022 -0.0102 0.0014 1.0000 11.500 1.3072 0.02608 0.02167 -0.0079 0.0014 1.0000 11.750 1.3162 0.02730 0.02308 -0.0056 0.0014 1.0000 12.000 1.3211 0.02862 0.02455 -0.0027 0.0014 1.0000 12.250 1.3171 0.03028 0.02638 0.0013 0.0014 1.0000 12.500 1.3145 0.03202 0.02829 0.0044 0.0014 1.0000 12.750 1.3120 0.03391 0.03034 0.0068 0.0013 1.0000 13.000 1.3052 0.03649 0.03310 0.0085 0.0013 1.0000 13.250 1.3003 0.03924 0.03602 0.0092 0.0012 1.0000 13.500 1.2870 0.04351 0.04048 0.0084 0.0013 1.0000 13.750 1.2657 0.05000 0.04719 0.0051 0.0013 1.0000 14.000 1.2559 0.05556 0.05292 0.0016 0.0013 1.0000 14.250 1.2486 0.06117 0.05867 -0.0020 0.0012 1.0000 14.500 1.2156 0.07180 0.06947 -0.0087 0.0013 1.0000 14.750 1.2048 0.07799 0.07576 -0.0122 0.0013 1.0000 15.000 1.1757 0.08777 0.08566 -0.0174 0.0013 1.0000 15.250 1.1459 0.09803 0.09603 -0.0227 0.0013 1.0000 15.500 1.1172 0.10840 0.10649 -0.0277 0.0014 1.0000 15.750 1.0923 0.11835 0.11651 -0.0323 0.0013 1.0000 16.000 1.0645 0.12940 0.12759 -0.0375 0.0014 1.0000 16.250 1.0294 0.14285 0.14112 -0.0437 0.0015 1.0000 16.500 1.0058 0.15427 0.15261 -0.0487 0.0015 1.0000