XFOIL Version 6.96 Calculated polar for: NACA 66(4)-221 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.8469 0.08124 0.07613 -0.1035 0.8716 0.0169 -19.500 -0.8495 0.07780 0.07254 -0.1047 0.8653 0.0169 -19.250 -0.8507 0.07455 0.06914 -0.1058 0.8601 0.0170 -19.000 -0.8510 0.07149 0.06595 -0.1069 0.8551 0.0171 -18.750 -0.8509 0.06855 0.06286 -0.1077 0.8500 0.0172 -18.500 -0.8490 0.06594 0.06012 -0.1083 0.8452 0.0173 -18.250 -0.8461 0.06349 0.05756 -0.1088 0.8411 0.0173 -18.000 -0.8430 0.06106 0.05501 -0.1092 0.8369 0.0174 -17.750 -0.8393 0.05881 0.05269 -0.1095 0.8326 0.0175 -17.500 -0.8356 0.05663 0.05044 -0.1097 0.8285 0.0177 -17.000 -0.8243 0.05273 0.04636 -0.1098 0.8213 0.0179 -16.750 -0.8177 0.05091 0.04448 -0.1098 0.8177 0.0181 -16.500 -0.8108 0.04917 0.04265 -0.1097 0.8141 0.0182 -16.250 -0.8033 0.04755 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0.6985 0.7203 2.750 0.4661 0.01064 0.00512 -0.0410 0.6970 0.7210 3.000 0.4899 0.01066 0.00521 -0.0406 0.6950 0.7218 3.250 0.5136 0.01066 0.00527 -0.0401 0.6920 0.7226 3.500 0.5391 0.01061 0.00527 -0.0399 0.6884 0.7233 3.750 0.5666 0.01054 0.00523 -0.0401 0.6853 0.7240 4.000 0.5953 0.01047 0.00518 -0.0406 0.6825 0.7247 4.250 0.6234 0.01041 0.00514 -0.0409 0.6788 0.7254 4.500 0.6409 0.01040 0.00522 -0.0391 0.6726 0.7263 4.750 0.6647 0.01028 0.00511 -0.0385 0.6657 0.7271 5.000 0.6830 0.01025 0.00513 -0.0368 0.6578 0.7280 5.250 0.7007 0.01016 0.00504 -0.0350 0.6467 0.7290 5.500 0.7018 0.01016 0.00508 -0.0299 0.6308 0.7302 5.750 0.6994 0.01035 0.00522 -0.0243 0.5991 0.7315 6.000 0.6790 0.01112 0.00567 -0.0157 0.5459 0.7331 6.250 0.6572 0.01234 0.00663 -0.0076 0.4996 0.7347 6.500 0.6387 0.01372 0.00778 -0.0007 0.4543 0.7362 6.750 0.6293 0.01497 0.00885 0.0046 0.4168 0.7375 7.000 0.6236 0.01619 0.00989 0.0090 0.3803 0.7388 7.250 0.6212 0.01735 0.01089 0.0128 0.3449 0.7399 7.500 0.6198 0.01852 0.01189 0.0163 0.3079 0.7414 7.750 0.6226 0.01957 0.01279 0.0192 0.2724 0.7429 8.000 0.6246 0.02072 0.01375 0.0220 0.2334 0.7443 8.250 0.6297 0.02176 0.01461 0.0244 0.1949 0.7457 8.500 0.6356 0.02281 0.01548 0.0266 0.1584 0.7471 8.750 0.6413 0.02391 0.01638 0.0287 0.1197 0.7485 9.000 0.6510 0.02484 0.01716 0.0303 0.0928 0.7499 9.250 0.6615 0.02577 0.01797 0.0318 0.0712 0.7513 9.500 0.6731 0.02667 0.01877 0.0331 0.0541 0.7527 9.750 0.6871 0.02745 0.01951 0.0340 0.0447 0.7542 10.000 0.7020 0.02819 0.02022 0.0349 0.0385 0.7556 10.250 0.7172 0.02894 0.02096 0.0357 0.0347 0.7569 10.500 0.7325 0.02971 0.02172 0.0364 0.0318 0.7582 10.750 0.7477 0.03046 0.02250 0.0372 0.0299 0.7598 11.000 0.7629 0.03122 0.02330 0.0379 0.0281 0.7614 11.250 0.7776 0.03202 0.02413 0.0386 0.0268 0.7630 11.500 0.7926 0.03283 0.02499 0.0393 0.0252 0.7648 11.750 0.8069 0.03370 0.02589 0.0400 0.0239 0.7666 12.000 0.8205 0.03464 0.02685 0.0408 0.0228 0.7685 12.250 0.8349 0.03554 0.02779 0.0414 0.0223 0.7705 12.500 0.8492 0.03646 0.02876 0.0420 0.0212 0.7725 12.750 0.8625 0.03747 0.02981 0.0426 0.0205 0.7745 13.000 0.8748 0.03857 0.03092 0.0432 0.0196 0.7763 13.250 0.8873 0.03966 0.03206 0.0438 0.0190 0.7782 13.500 0.9003 0.04073 0.03319 0.0444 0.0186 0.7804 13.750 0.9118 0.04192 0.03445 0.0450 0.0182 0.7826 14.000 0.9235 0.04312 0.03571 0.0455 0.0175 0.7851 14.250 0.9354 0.04434 0.03698 0.0460 0.0169 0.7876 14.500 0.9452 0.04575 0.03844 0.0465 0.0168 0.7902 14.750 0.9544 0.04722 0.03996 0.0470 0.0164 0.7929 15.000 0.9627 0.04885 0.04163 0.0475 0.0161 0.7954 15.250 0.9728 0.05033 0.04319 0.0478 0.0158 0.7980 15.500 0.9811 0.05195 0.04491 0.0483 0.0156 0.8011 15.750 0.9889 0.05367 0.04671 0.0486 0.0154 0.8042 16.000 0.9968 0.05543 0.04856 0.0488 0.0152 0.8075 16.250 1.0035 0.05733 0.05054 0.0490 0.0150 0.8108 16.500 1.0114 0.05919 0.05246 0.0491 0.0147 0.8139 16.750 1.0176 0.06125 0.05460 0.0491 0.0145 0.8168 17.000 1.0229 0.06339 0.05684 0.0491 0.0145 0.8201 17.250 1.0283 0.06559 0.05912 0.0490 0.0143 0.8236 17.500 1.0337 0.06784 0.06146 0.0488 0.0141 0.8274 17.750 1.0385 0.07022 0.06391 0.0485 0.0140 0.8311 18.000 1.0414 0.07285 0.06662 0.0481 0.0139 0.8345 18.250 1.0439 0.07554 0.06940 0.0476 0.0138 0.8383 18.500 1.0461 0.07833 0.07228 0.0471 0.0136 0.8424 18.750 1.0472 0.08130 0.07534 0.0464 0.0135 0.8467 19.000 1.0486 0.08431 0.07845 0.0456 0.0134 0.8508 19.250 1.0494 0.08739 0.08163 0.0447 0.0133 0.8550