XFOIL Version 6.96 Calculated polar for: NACA 66-018 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 ------ -------- --------- --------- -------- -------- -------- -19.250 -1.1365 0.07198 0.06792 -0.0594 0.9663 0.0104 -19.000 -1.1251 0.06793 0.06375 -0.0639 0.9592 0.0105 -18.750 -1.1184 0.06354 0.05919 -0.0682 0.9525 0.0105 -18.500 -1.1058 0.06008 0.05559 -0.0720 0.9417 0.0106 -18.250 -1.0966 0.05740 0.05277 -0.0739 0.9271 0.0107 -18.000 -1.0935 0.05487 0.05010 -0.0744 0.9122 0.0108 -17.750 -1.0923 0.05244 0.04753 -0.0743 0.8986 0.0108 -17.500 -1.0875 0.05047 0.04544 -0.0742 0.8870 0.0109 -17.250 -1.0844 0.04836 0.04321 -0.0738 0.8777 0.0110 -16.750 -1.0741 0.04470 0.03933 -0.0730 0.8630 0.0110 -16.500 -1.0683 0.04298 0.03752 -0.0724 0.8566 0.0112 -16.250 -1.0645 0.04116 0.03559 -0.0717 0.8509 0.0113 -16.000 -1.0584 0.03951 0.03386 -0.0710 0.8460 0.0113 -15.750 -1.0505 0.03806 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0.0026 0.7123 0.6994 -1.000 -0.1171 0.00642 0.00193 0.0022 0.7114 0.7026 -0.750 -0.0880 0.00642 0.00195 0.0017 0.7105 0.7050 -0.500 -0.0587 0.00642 0.00194 0.0011 0.7097 0.7063 -0.250 -0.0293 0.00642 0.00194 0.0006 0.7088 0.7071 0.000 0.0000 0.00642 0.00194 0.0000 0.7080 0.7080 0.250 0.0293 0.00642 0.00194 -0.0006 0.7072 0.7088 0.500 0.0587 0.00642 0.00195 -0.0011 0.7063 0.7097 0.750 0.0880 0.00642 0.00195 -0.0017 0.7050 0.7105 1.000 0.1171 0.00641 0.00194 -0.0022 0.7026 0.7114 1.250 0.1461 0.00642 0.00192 -0.0026 0.6995 0.7123 1.500 0.1751 0.00643 0.00192 -0.0031 0.6965 0.7132 1.750 0.2039 0.00641 0.00193 -0.0035 0.6934 0.7139 2.000 0.2327 0.00639 0.00193 -0.0039 0.6889 0.7146 2.250 0.2611 0.00637 0.00190 -0.0042 0.6830 0.7156 2.500 0.2894 0.00635 0.00191 -0.0045 0.6755 0.7166 2.750 0.3174 0.00635 0.00191 -0.0048 0.6676 0.7176 3.000 0.3452 0.00635 0.00193 -0.0050 0.6567 0.7186 3.250 0.3705 0.00640 0.00192 -0.0047 0.6283 0.7196 3.500 0.3708 0.00732 0.00225 0.0004 0.4923 0.7210 3.750 0.3735 0.00813 0.00267 0.0048 0.3977 0.7225 4.000 0.3791 0.00874 0.00299 0.0087 0.3289 0.7239 4.250 0.3861 0.00918 0.00324 0.0123 0.2832 0.7253 4.500 0.3849 0.00968 0.00354 0.0176 0.2343 0.7268 4.750 0.3894 0.01025 0.00394 0.0215 0.1913 0.7282 5.000 0.3973 0.01081 0.00433 0.0246 0.1534 0.7296 5.250 0.4061 0.01140 0.00474 0.0275 0.1146 0.7307 5.500 0.4168 0.01194 0.00516 0.0300 0.0833 0.7323 5.750 0.4310 0.01239 0.00553 0.0319 0.0635 0.7341 6.000 0.4460 0.01283 0.00590 0.0336 0.0473 0.7357 6.250 0.4636 0.01319 0.00623 0.0349 0.0395 0.7374 6.500 0.4812 0.01356 0.00657 0.0361 0.0339 0.7391 6.750 0.5003 0.01388 0.00690 0.0371 0.0310 0.7407 7.000 0.5188 0.01424 0.00724 0.0382 0.0287 0.7424 7.250 0.5379 0.01457 0.00758 0.0392 0.0271 0.7440 7.500 0.5567 0.01494 0.00794 0.0401 0.0253 0.7455 7.750 0.5753 0.01532 0.00832 0.0411 0.0240 0.7469 8.000 0.5943 0.01568 0.00869 0.0420 0.0227 0.7485 8.250 0.6127 0.01605 0.00908 0.0430 0.0214 0.7504 8.500 0.6306 0.01646 0.00949 0.0441 0.0205 0.7523 8.750 0.6488 0.01686 0.00992 0.0450 0.0198 0.7544 9.000 0.6671 0.01727 0.01036 0.0460 0.0191 0.7565 9.250 0.6853 0.01769 0.01080 0.0469 0.0184 0.7586 9.500 0.7034 0.01813 0.01124 0.0478 0.0177 0.7607 9.750 0.7203 0.01863 0.01175 0.0488 0.0170 0.7627 10.000 0.7373 0.01915 0.01229 0.0498 0.0166 0.7645 10.250 0.7549 0.01961 0.01279 0.0507 0.0163 0.7668 10.500 0.7724 0.02009 0.01330 0.0516 0.0157 0.7693 10.750 0.7885 0.02064 0.01390 0.0526 0.0156 0.7718 11.000 0.8052 0.02118 0.01447 0.0535 0.0152 0.7745 11.250 0.8214 0.02175 0.01507 0.0545 0.0149 0.7771 11.500 0.8377 0.02234 0.01568 0.0553 0.0146 0.7796 11.750 0.8530 0.02300 0.01636 0.0563 0.0142 0.7819 12.000 0.8664 0.02376 0.01716 0.0575 0.0138 0.7849 12.250 0.8815 0.02442 0.01788 0.0584 0.0136 0.7882 12.500 0.8954 0.02518 0.01869 0.0595 0.0135 0.7916 12.750 0.9103 0.02589 0.01945 0.0603 0.0133 0.7949 13.000 0.9247 0.02665 0.02026 0.0612 0.0132 0.7981 13.250 0.9391 0.02741 0.02107 0.0620 0.0130 0.8011 13.500 0.9518 0.02828 0.02200 0.0630 0.0128 0.8046 13.750 0.9657 0.02909 0.02287 0.0638 0.0125 0.8083 14.000 0.9779 0.03004 0.02388 0.0647 0.0125 0.8120 14.250 0.9906 0.03098 0.02487 0.0654 0.0123 0.8155 14.500 1.0021 0.03201 0.02596 0.0663 0.0122 0.8190 14.750 1.0137 0.03303 0.02705 0.0671 0.0120 0.8233 15.000 1.0249 0.03411 0.02818 0.0679 0.0117 0.8277 15.250 1.0352 0.03530 0.02944 0.0686 0.0118 0.8319 15.500 1.0447 0.03656 0.03076 0.0694 0.0116 0.8360 15.750 1.0530 0.03790 0.03218 0.0701 0.0115 0.8410 16.000 1.0589 0.03951 0.03386 0.0710 0.0112 0.8462 16.250 1.0650 0.04115 0.03558 0.0716 0.0112 0.8511 16.500 1.0707 0.04282 0.03735 0.0723 0.0112 0.8569 16.750 1.0725 0.04489 0.03952 0.0730 0.0110 0.8633 17.250 1.0837 0.04849 0.04334 0.0738 0.0110 0.8782 17.750 1.0928 0.05245 0.04754 0.0743 0.0108 0.8994 18.000 1.0967 0.05461 0.04983 0.0742 0.0107 0.9135 18.250 1.1005 0.05711 0.05247 0.0737 0.0107 0.9285 18.500 1.1093 0.05998 0.05549 0.0715 0.0106 0.9430 18.750 1.1238 0.06332 0.05897 0.0675 0.0104 0.9531 19.000 1.1366 0.06713 0.06292 0.0631 0.0104 0.9600 19.250 1.1451 0.07147 0.06740 0.0586 0.0104 0.9670