XFOIL Version 6.94 Calculated polar for: DAE-31 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.7269 0.01359 0.00666 -0.1566 0.7425 0.0805 0.500 0.7817 0.01243 0.00640 -0.1566 0.7333 0.3760 1.000 0.8408 0.01092 0.00604 -0.1565 0.7264 1.0000 1.500 0.8934 0.01100 0.00599 -0.1557 0.7146 1.0000 2.000 0.9528 0.01081 0.00557 -0.1558 0.7054 1.0000 2.500 1.0053 0.01087 0.00556 -0.1550 0.6917 1.0000 3.000 1.0612 0.01084 0.00540 -0.1546 0.6792 1.0000 3.500 1.1152 0.01086 0.00532 -0.1540 0.6643 1.0000 4.000 1.1665 0.01099 0.00542 -0.1529 0.6467 1.0000 4.500 1.2174 0.01116 0.00551 -0.1518 0.6272 1.0000 5.000 1.2668 0.01141 0.00570 -0.1505 0.6058 1.0000 5.500 1.3140 0.01176 0.00596 -0.1488 0.5824 1.0000 6.000 1.3586 0.01222 0.00634 -0.1467 0.5573 1.0000 6.500 1.3994 0.01281 0.00683 -0.1440 0.5308 1.0000 7.000 1.4347 0.01349 0.00747 -0.1405 0.5028 1.0000 7.500 1.4630 0.01429 0.00821 -0.1357 0.4744 1.0000 8.000 1.4812 0.01527 0.00909 -0.1292 0.4472 1.0000 8.500 1.4984 0.01645 0.01024 -0.1232 0.4199 1.0000 9.000 1.5149 0.01787 0.01162 -0.1175 0.3912 1.0000 9.500 1.5293 0.01961 0.01328 -0.1121 0.3626 1.0000 10.000 1.5434 0.02158 0.01520 -0.1070 0.3345 1.0000 10.500 1.5579 0.02373 0.01731 -0.1024 0.3060 1.0000 11.000 1.5694 0.02623 0.01975 -0.0979 0.2787 1.0000 11.500 1.5799 0.02900 0.02247 -0.0937 0.2531 1.0000 12.000 1.5920 0.03186 0.02534 -0.0900 0.2284 1.0000 12.500 1.6021 0.03509 0.02856 -0.0866 0.2054 1.0000 13.000 1.6111 0.03864 0.03211 -0.0835 0.1849 1.0000 13.500 1.6196 0.04248 0.03597 -0.0808 0.1669 1.0000 14.000 1.6272 0.04665 0.04019 -0.0785 0.1505 1.0000 14.500 1.6332 0.05123 0.04483 -0.0765 0.1354 1.0000 15.000 1.6363 0.05638 0.05003 -0.0750 0.1207 1.0000 15.500 1.6380 0.06199 0.05572 -0.0740 0.1068 1.0000 16.000 1.6395 0.06793 0.06178 -0.0735 0.0941 1.0000 16.500 1.6377 0.07456 0.06855 -0.0735 0.0829 1.0000 17.000 1.6328 0.08196 0.07607 -0.0741 0.0727 1.0000 17.500 1.6248 0.09011 0.08436 -0.0754 0.0636 1.0000 18.000 1.6133 0.09913 0.09351 -0.0774 0.0559 1.0000 18.500 1.6005 0.10862 0.10315 -0.0802 0.0493 1.0000 19.000 1.5878 0.11831 0.11300 -0.0835 0.0437 1.0000 19.500 1.5752 0.12814 0.12300 -0.0874 0.0388 1.0000 20.000 1.5633 0.13790 0.13293 -0.0917 0.0347 1.0000 20.500 1.5525 0.14746 0.14263 -0.0964 0.0313 1.0000 21.000 1.5441 0.15646 0.15171 -0.1011 0.0286 1.0000 21.500 1.5390 0.16497 0.16042 -0.1058 0.0261 1.0000 22.000 1.5374 0.17246 0.16800 -0.1102 0.0242 1.0000 22.500 1.5367 0.17988 0.17558 -0.1147 0.0226 1.0000 23.000 1.5434 0.18521 0.18092 -0.1179 0.0212 1.0000 23.500 1.5398 0.19331 0.18931 -0.1234 0.0203 1.0000 24.000 1.5385 0.20072 0.19691 -0.1285 0.0194 1.0000 24.500 1.5426 0.20665 0.20294 -0.1328 0.0187 1.0000 25.000 1.5454 0.21251 0.20892 -0.1371 0.0181 1.0000 25.500 1.5272 0.22420 0.22097 -0.1461 0.0179 1.0000 26.000 1.4982 0.23918 0.23632 -0.1575 0.0179 1.0000 26.500 1.3350 0.32045 0.31782 -0.2016 0.0293 1.0000 27.500 1.3498 0.33431 0.33170 -0.2120 0.0262 1.0000 28.000 1.3616 0.33814 0.33558 -0.2151 0.0253 1.0000 28.500 1.3679 0.34555 0.34299 -0.2207 0.0243 1.0000 29.000 1.3770 0.35071 0.34818 -0.2251 0.0223 1.0000 29.500 1.0582 0.45577 0.45430 -0.2179 0.0166 1.0000 30.000 1.0625 0.46303 0.46162 -0.2198 0.0153 1.0000 30.500 1.0611 0.47953 0.47812 -0.2237 0.0135 1.0000 31.000 1.0634 0.48839 0.48703 -0.2260 0.0127 1.0000 31.500 1.0630 0.50417 0.50281 -0.2293 0.0113 1.0000 32.000 1.0641 0.51349 0.51218 -0.2318 0.0103 1.0000 32.500 1.0639 0.52786 0.52656 -0.2347 0.0096 1.0000 33.000 1.0641 0.53930 0.53804 -0.2373 0.0084 1.0000 33.500 1.0643 0.54902 0.54779 -0.2395 0.0079 1.0000 34.000 1.0635 0.56475 0.56354 -0.2425 0.0072 1.0000 34.500 1.0627 0.57593 0.57475 -0.2450 0.0065 1.0000 35.000 1.0616 0.58518 0.58404 -0.2472 0.0061 1.0000 35.500 1.0602 0.59967 0.59855 -0.2499 0.0058 1.0000 36.000 1.0587 0.61179 0.61070 -0.2522 0.0050 1.0000 36.500 1.0567 0.62192 0.62086 -0.2545 0.0045 1.0000 37.000 1.0543 0.63056 0.62953 -0.2565 0.0043 1.0000 37.500 1.0522 0.64656 0.64554 -0.2590 0.0041 1.0000 38.000 1.0496 0.65829 0.65730 -0.2612 0.0035 1.0000 38.500 1.0465 0.66878 0.66783 -0.2634 0.0032 1.0000 39.000 1.0427 0.67792 0.67700 -0.2655 0.0029 1.0000 40.000 1.0348 0.69951 0.69864 -0.2696 0.0028 1.0000 40.500 1.0314 0.71209 0.71124 -0.2715 0.0025 1.0000 41.000 1.0270 0.72208 0.72126 -0.2735 0.0022 1.0000 41.500 1.0219 0.73084 0.73006 -0.2754 0.0018 1.0000 42.000 1.0163 0.73888 0.73813 -0.2773 0.0016 1.0000 43.000 1.0061 0.76015 0.75944 -0.2808 0.0015 1.0000 43.500 1.0007 0.76994 0.76926 -0.2824 0.0012 1.0000 44.000 0.9945 0.77815 0.77750 -0.2841 0.0010 1.0000 44.500 0.9879 0.78550 0.78487 -0.2857 0.0009 1.0000 45.000 0.9809 0.79230 0.79171 -0.2873 0.0008 1.0000 45.500 0.9729 0.79776 0.79719 -0.2889 0.0007 1.0000 46.500 0.9589 0.81362 0.81310 -0.2918 0.0006 1.0000 47.000 0.9517 0.82086 0.82036 -0.2931 0.0006 1.0000 47.500 0.9438 0.82652 0.82605 -0.2945 0.0006 1.0000 48.000 0.9358 0.83204 0.83160 -0.2958 0.0005 1.0000 48.500 0.9273 0.83685 0.83644 -0.2970 0.0004 1.0000 49.000 0.9186 0.84108 0.84069 -0.2982 0.0002 1.0000 49.500 0.9096 0.84466 0.84430 -0.2995 0.0002 1.0000 50.000 0.9000 0.84718 0.84684 -0.3007 0.0001 1.0000 50.500 0.8899 0.84899 0.84868 -0.3018 0.0001 1.0000 51.000 0.8813 0.85378 0.85349 -0.3027 0.0001 1.0000 51.500 0.8724 0.85764 0.85737 -0.3035 0.0000 1.0000 52.000 0.8624 0.85896 0.85871 -0.3045 0.0000 1.0000 53.500 0.8318 0.86219 0.86200 -0.3070 0.0000 1.0000 54.000 0.8213 0.86220 0.86204 -0.3077 0.0000 1.0000 54.500 0.8104 0.86122 0.86107 -0.3085 0.0000 1.0000 55.000 0.7996 0.86026 0.86014 -0.3091 0.0000 1.0000 55.500 0.7883 0.85811 0.85801 -0.3097 0.0000 1.0000 56.000 0.7770 0.85573 0.85565 -0.3103 0.0000 1.0000