XFOIL Version 6.96 Calculated polar for: NACA 67 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.750 -0.8424 0.07834 0.07591 -0.0928 0.9792 0.0130 -17.500 -0.8709 0.06754 0.06487 -0.1013 0.9773 0.0130 -17.250 -0.8867 0.05961 0.05672 -0.1081 0.9752 0.0130 -17.000 -0.8926 0.05373 0.05064 -0.1133 0.9727 0.0131 -16.750 -0.8945 0.04887 0.04559 -0.1175 0.9698 0.0132 -16.500 -0.8950 0.04466 0.04119 -0.1208 0.9664 0.0133 -16.250 -0.8874 0.04167 0.03805 -0.1235 0.9626 0.0136 -16.000 -0.8858 0.03853 0.03471 -0.1250 0.9577 0.0136 -15.750 -0.8849 0.03615 0.03215 -0.1250 0.9516 0.0136 -15.500 -0.8793 0.03439 0.03024 -0.1247 0.9461 0.0139 -15.250 -0.8744 0.03311 0.02886 -0.1235 0.9407 0.0140 -15.000 -0.8708 0.03170 0.02730 -0.1220 0.9355 0.0142 -14.750 -0.8682 0.03010 0.02554 -0.1203 0.9306 0.0142 -14.500 -0.8629 0.02896 0.02429 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-5.000 -0.2182 0.01029 0.00414 -0.0714 0.8560 0.0623 -4.750 -0.1994 0.01005 0.00398 -0.0699 0.8549 0.0786 -4.500 -0.1848 0.00976 0.00386 -0.0677 0.8535 0.1169 -4.250 -0.1732 0.00941 0.00372 -0.0649 0.8526 0.1656 -4.000 -0.1657 0.00906 0.00362 -0.0611 0.8511 0.2250 -3.750 -0.1594 0.00868 0.00352 -0.0571 0.8496 0.2972 -3.500 -0.1543 0.00819 0.00339 -0.0529 0.8481 0.3873 -3.250 -0.1516 0.00762 0.00322 -0.0482 0.8464 0.4924 -3.000 -0.1513 0.00690 0.00298 -0.0428 0.8445 0.6153 -2.750 -0.1424 0.00644 0.00299 -0.0389 0.8431 0.7347 -2.500 -0.1164 0.00650 0.00308 -0.0386 0.8423 0.7637 -2.250 -0.0892 0.00658 0.00313 -0.0386 0.8415 0.7777 -2.000 -0.0607 0.00665 0.00321 -0.0389 0.8407 0.7852 -1.750 -0.0332 0.00676 0.00327 -0.0389 0.8397 0.7934 -1.500 -0.0046 0.00694 0.00348 -0.0391 0.8387 0.8012 -1.250 0.0216 0.00716 0.00370 -0.0388 0.8376 0.8109 -1.000 0.0500 0.00748 0.00409 -0.0387 0.8368 0.8207 -0.750 0.0771 0.00774 0.00439 -0.0384 0.8356 0.8286 -0.500 0.1058 0.00800 0.00469 -0.0385 0.8344 0.8331 -0.250 0.1330 0.00810 0.00479 -0.0385 0.8330 0.8359 0.000 0.1600 0.00810 0.00479 -0.0386 0.8316 0.8375 0.250 0.1876 0.00808 0.00477 -0.0388 0.8301 0.8389 0.500 0.2161 0.00803 0.00470 -0.0391 0.8285 0.8401 0.750 0.2471 0.00791 0.00455 -0.0399 0.8263 0.8409 1.000 0.2799 0.00774 0.00435 -0.0411 0.8235 0.8418 1.250 0.3053 0.00758 0.00421 -0.0406 0.8190 0.8429 1.500 0.3336 0.00738 0.00402 -0.0408 0.8142 0.8438 1.750 0.3661 0.00717 0.00377 -0.0418 0.8095 0.8445 2.000 0.3925 0.00704 0.00365 -0.0415 0.8032 0.8454 2.250 0.4204 0.00683 0.00343 -0.0415 0.7953 0.8461 2.500 0.4458 0.00670 0.00330 -0.0410 0.7867 0.8470 2.750 0.4719 0.00659 0.00319 -0.0407 0.7783 0.8479 3.000 0.4954 0.00653 0.00317 -0.0399 0.7680 0.8490 3.250 0.5196 0.00647 0.00311 -0.0393 0.7559 0.8500 3.500 0.5410 0.00642 0.00303 -0.0380 0.7336 0.8511 3.750 0.5484 0.00658 0.00296 -0.0336 0.6770 0.8526 4.000 0.5357 0.00698 0.00306 -0.0251 0.6136 0.8549 4.250 0.5193 0.00754 0.00335 -0.0160 0.5515 0.8569 4.500 0.5098 0.00818 0.00372 -0.0088 0.4880 0.8591 4.750 0.5069 0.00885 0.00413 -0.0031 0.4236 0.8609 5.000 0.5072 0.00956 0.00455 0.0018 0.3543 0.8625 5.250 0.5132 0.01020 0.00492 0.0055 0.2903 0.8640 5.500 0.5210 0.01085 0.00529 0.0088 0.2274 0.8657 5.750 0.5326 0.01142 0.00563 0.0114 0.1757 0.8672 6.000 0.5463 0.01195 0.00595 0.0135 0.1329 0.8686 6.250 0.5611 0.01245 0.00628 0.0154 0.0958 0.8698 6.500 0.5768 0.01294 0.00660 0.0171 0.0678 0.8710 6.750 0.5950 0.01334 0.00692 0.0184 0.0544 0.8721 7.000 0.6153 0.01364 0.00720 0.0193 0.0492 0.8730 7.250 0.6350 0.01396 0.00750 0.0204 0.0445 0.8741 7.500 0.6553 0.01422 0.00778 0.0213 0.0419 0.8755 7.750 0.6745 0.01457 0.00812 0.0224 0.0391 0.8769 8.000 0.6938 0.01492 0.00849 0.0235 0.0370 0.8782 8.250 0.7143 0.01521 0.00880 0.0243 0.0355 0.8796 8.500 0.7343 0.01554 0.00914 0.0253 0.0336 0.8812 8.750 0.7514 0.01603 0.00964 0.0266 0.0312 0.8828 9.000 0.7721 0.01631 0.00994 0.0274 0.0300 0.8842 9.250 0.7921 0.01663 0.01028 0.0282 0.0285 0.8858 9.500 0.8105 0.01707 0.01071 0.0292 0.0263 0.8873 9.750 0.8289 0.01752 0.01118 0.0303 0.0248 0.8887 10.000 0.8487 0.01785 0.01154 0.0311 0.0233 0.8903 10.250 0.8661 0.01831 0.01201 0.0323 0.0218 0.8923 10.500 0.8816 0.01890 0.01264 0.0337 0.0206 0.8943 10.750 0.9007 0.01927 0.01304 0.0346 0.0192 0.8962 11.000 0.9186 0.01973 0.01353 0.0356 0.0184 0.8982 11.250 0.9333 0.02041 0.01422 0.0371 0.0175 0.9005 11.500 0.9474 0.02110 0.01497 0.0386 0.0168 0.9028 11.750 0.9643 0.02164 0.01555 0.0396 0.0164 0.9048 12.000 0.9789 0.02228 0.01626 0.0410 0.0160 0.9077 12.250 0.9951 0.02280 0.01683 0.0422 0.0154 0.9104 12.500 1.0075 0.02358 0.01768 0.0438 0.0152 0.9135 12.750 1.0228 0.02420 0.01834 0.0449 0.0148 0.9164 13.000 1.0359 0.02498 0.01916 0.0463 0.0145 0.9193 13.250 1.0441 0.02605 0.02029 0.0482 0.0140 0.9228 13.500 1.0509 0.02723 0.02157 0.0503 0.0137 0.9264 13.750 1.0623 0.02811 0.02252 0.0518 0.0136 0.9302 14.000 1.0740 0.02898 0.02347 0.0531 0.0134 0.9339 14.250 1.0831 0.03004 0.02464 0.0547 0.0132 0.9383 14.500 1.0928 0.03105 0.02574 0.0561 0.0131 0.9432 14.750 1.1011 0.03223 0.02701 0.0576 0.0129 0.9483 15.000 1.1097 0.03350 0.02840 0.0588 0.0128 0.9544 15.250 1.1216 0.03474 0.02973 0.0592 0.0125 0.9611 15.500 1.1352 0.03641 0.03153 0.0587 0.0124 0.9673 15.750 1.1504 0.03822 0.03345 0.0576 0.0122 0.9721 16.000 1.1660 0.04016 0.03548 0.0561 0.0120 0.9781 16.250 1.1776 0.04230 0.03774 0.0549 0.0119 0.9942 16.500 1.1804 0.04421 0.03971 0.0560 0.0117 1.0000 16.750 1.1827 0.04641 0.04198 0.0566 0.0116 1.0000 17.000 1.1816 0.04901 0.04469 0.0572 0.0115 1.0000 17.250 1.1812 0.05164 0.04741 0.0574 0.0115 1.0000 17.500 1.1777 0.05471 0.05059 0.0575 0.0113 1.0000 17.750 1.1702 0.05837 0.05437 0.0574 0.0112 1.0000 18.000 1.1645 0.06198 0.05811 0.0570 0.0112 1.0000 18.250 1.1506 0.06677 0.06305 0.0561 0.0111 1.0000 18.500 1.1470 0.07049 0.06689 0.0550 0.0112 1.0000 18.750 1.1256 0.07683 0.07341 0.0529 0.0110 1.0000 19.000 1.1084 0.08292 0.07966 0.0504 0.0110 1.0000