XFOIL Version 6.96 Calculated polar for: NACA 66(3)-418 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 ------ -------- --------- --------- -------- -------- -------- -17.750 -0.6241 0.08951 0.08630 -0.1079 0.9430 0.0161 -17.500 -0.6700 0.07553 0.07197 -0.1181 0.9367 0.0162 -17.250 -0.6898 0.06736 0.06353 -0.1245 0.9278 0.0162 -17.000 -0.7040 0.06133 0.05724 -0.1285 0.9172 0.0162 -16.750 -0.7140 0.05685 0.05254 -0.1306 0.9069 0.0163 -16.500 -0.7235 0.05292 0.04839 -0.1319 0.8977 0.0164 -16.250 -0.7318 0.04954 0.04480 -0.1323 0.8892 0.0166 -15.750 -0.7394 0.04425 0.03914 -0.1320 0.8747 0.0167 -15.500 -0.7399 0.04215 0.03685 -0.1315 0.8681 0.0170 -15.250 -0.7387 0.04026 0.03478 -0.1308 0.8622 0.0172 -15.000 -0.7368 0.03837 0.03272 -0.1300 0.8566 0.0173 -14.750 -0.7331 0.03677 0.03095 -0.1290 0.8510 0.0175 -14.500 -0.7276 0.03528 0.02929 -0.1281 0.8464 0.0176 -14.250 -0.7209 0.03384 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0.0497 -4.750 -0.1178 0.01245 0.00479 -0.0851 0.7489 0.0608 -4.500 -0.1006 0.01213 0.00456 -0.0836 0.7475 0.0848 -4.250 -0.0857 0.01169 0.00431 -0.0817 0.7462 0.1320 -4.000 -0.0725 0.01114 0.00404 -0.0797 0.7449 0.2047 -3.750 -0.0589 0.01055 0.00377 -0.0777 0.7436 0.2858 -3.500 -0.0464 0.00985 0.00347 -0.0757 0.7423 0.3850 -3.250 -0.0341 0.00899 0.00311 -0.0736 0.7409 0.5054 -3.000 -0.0166 0.00852 0.00318 -0.0720 0.7397 0.6415 -2.750 0.0107 0.00860 0.00330 -0.0720 0.7385 0.6737 -2.500 0.0385 0.00874 0.00346 -0.0721 0.7374 0.6923 -2.250 0.0666 0.00888 0.00356 -0.0723 0.7364 0.7053 -2.000 0.0949 0.00905 0.00378 -0.0724 0.7353 0.7138 -1.750 0.1234 0.00912 0.00382 -0.0727 0.7343 0.7190 -1.500 0.1521 0.00916 0.00380 -0.0732 0.7333 0.7227 -1.250 0.1808 0.00920 0.00384 -0.0735 0.7323 0.7253 -1.000 0.2096 0.00923 0.00387 -0.0740 0.7313 0.7273 -0.750 0.2386 0.00924 0.00386 -0.0745 0.7303 0.7286 -0.500 0.2678 0.00926 0.00385 -0.0750 0.7294 0.7295 -0.250 0.2972 0.00928 0.00385 -0.0757 0.7286 0.7305 0.000 0.3266 0.00932 0.00387 -0.0763 0.7277 0.7318 0.250 0.3547 0.00935 0.00390 -0.0767 0.7269 0.7329 0.500 0.3826 0.00937 0.00395 -0.0770 0.7259 0.7339 0.750 0.4105 0.00940 0.00399 -0.0774 0.7248 0.7350 1.000 0.4383 0.00943 0.00404 -0.0777 0.7235 0.7360 1.250 0.4661 0.00946 0.00407 -0.0780 0.7218 0.7370 1.500 0.4941 0.00946 0.00408 -0.0783 0.7196 0.7380 1.750 0.5225 0.00945 0.00408 -0.0787 0.7172 0.7390 2.000 0.5515 0.00944 0.00406 -0.0792 0.7149 0.7399 2.250 0.5807 0.00943 0.00405 -0.0798 0.7129 0.7408 2.500 0.6098 0.00946 0.00410 -0.0803 0.7110 0.7418 2.750 0.6348 0.00949 0.00421 -0.0800 0.7084 0.7430 3.000 0.6605 0.00950 0.00427 -0.0798 0.7048 0.7441 3.250 0.6873 0.00948 0.00428 -0.0799 0.7008 0.7451 3.500 0.7156 0.00944 0.00426 -0.0802 0.6972 0.7462 3.750 0.7410 0.00944 0.00430 -0.0799 0.6922 0.7473 4.000 0.7639 0.00941 0.00433 -0.0791 0.6850 0.7486 4.250 0.7898 0.00937 0.00428 -0.0788 0.6778 0.7498 4.500 0.8108 0.00938 0.00436 -0.0777 0.6690 0.7512 4.750 0.8306 0.00937 0.00436 -0.0762 0.6554 0.7526 5.000 0.8431 0.00938 0.00433 -0.0732 0.6270 0.7542 5.250 0.8303 0.00968 0.00434 -0.0651 0.5677 0.7563 5.500 0.8098 0.01065 0.00500 -0.0562 0.5125 0.7584 5.750 0.7962 0.01171 0.00584 -0.0491 0.4645 0.7604 6.000 0.7869 0.01284 0.00677 -0.0432 0.4199 0.7625 6.250 0.7811 0.01400 0.00774 -0.0382 0.3755 0.7646 6.500 0.7795 0.01513 0.00869 -0.0341 0.3344 0.7667 6.750 0.7794 0.01629 0.00964 -0.0304 0.2912 0.7691 7.000 0.7797 0.01750 0.01062 -0.0269 0.2435 0.7715 7.250 0.7839 0.01860 0.01151 -0.0241 0.2022 0.7736 7.500 0.7854 0.01990 0.01251 -0.0211 0.1493 0.7755 7.750 0.7911 0.02100 0.01342 -0.0187 0.1079 0.7774 8.000 0.8000 0.02198 0.01426 -0.0167 0.0793 0.7794 8.500 0.8246 0.02368 0.01580 -0.0137 0.0446 0.7835 8.750 0.8390 0.02444 0.01654 -0.0125 0.0372 0.7857 9.000 0.8548 0.02514 0.01724 -0.0116 0.0331 0.7880 9.250 0.8705 0.02587 0.01797 -0.0106 0.0298 0.7903 9.500 0.8866 0.02658 0.01869 -0.0097 0.0273 0.7926 9.750 0.9018 0.02734 0.01948 -0.0088 0.0255 0.7947 10.000 0.9176 0.02807 0.02026 -0.0079 0.0238 0.7970 10.250 0.9325 0.02887 0.02109 -0.0070 0.0225 0.7995 10.500 0.9474 0.02969 0.02195 -0.0060 0.0212 0.8022 10.750 0.9625 0.03051 0.02282 -0.0052 0.0199 0.8050 11.000 0.9769 0.03140 0.02374 -0.0044 0.0188 0.8078 11.250 0.9909 0.03235 0.02471 -0.0035 0.0178 0.8106 11.500 1.0053 0.03325 0.02568 -0.0027 0.0171 0.8132 11.750 1.0187 0.03422 0.02672 -0.0018 0.0163 0.8163 12.000 1.0322 0.03522 0.02776 -0.0010 0.0158 0.8196 12.250 1.0448 0.03630 0.02889 -0.0001 0.0155 0.8231 12.500 1.0558 0.03754 0.03017 0.0008 0.0148 0.8268 12.750 1.0681 0.03870 0.03141 0.0016 0.0145 0.8302 13.000 1.0798 0.03988 0.03268 0.0024 0.0141 0.8339 13.250 1.0904 0.04119 0.03406 0.0032 0.0138 0.8378 13.500 1.1014 0.04251 0.03545 0.0039 0.0136 0.8418 13.750 1.1121 0.04388 0.03689 0.0046 0.0133 0.8458 14.000 1.1213 0.04536 0.03845 0.0054 0.0131 0.8498 14.250 1.1306 0.04687 0.04004 0.0061 0.0130 0.8544 14.500 1.1390 0.04851 0.04175 0.0067 0.0127 0.8592 14.750 1.1461 0.05029 0.04360 0.0074 0.0125 0.8638 15.000 1.1523 0.05215 0.04555 0.0081 0.0123 0.8691 15.250 1.1572 0.05419 0.04768 0.0087 0.0122 0.8747 15.500 1.1643 0.05608 0.04967 0.0092 0.0121 0.8806 15.750 1.1701 0.05806 0.05178 0.0097 0.0120 0.8875 16.000 1.1756 0.06014 0.05396 0.0101 0.0119 0.8950 16.250 1.1801 0.06228 0.05622 0.0105 0.0117 0.9036 16.500 1.1841 0.06459 0.05865 0.0108 0.0117 0.9131 16.750 1.1880 0.06695 0.06113 0.0110 0.0116 0.9247 17.000 1.1924 0.06955 0.06386 0.0107 0.0114 0.9390 17.250 1.1998 0.07238 0.06683 0.0094 0.0113 0.9577 17.500 1.2021 0.07511 0.06967 0.0090 0.0113 1.0000 17.750 1.2041 0.07814 0.07279 0.0084 0.0111 1.0000 18.000 1.2061 0.08123 0.07598 0.0077 0.0110 1.0000 18.250 1.2078 0.08443 0.07927 0.0068 0.0110 1.0000 18.500 1.2085 0.08782 0.08277 0.0059 0.0109 1.0000 18.750 1.2084 0.09137 0.08642 0.0047 0.0108 1.0000 19.000 1.2081 0.09500 0.09016 0.0034 0.0107 1.0000 19.250 1.2066 0.09886 0.09412 0.0020 0.0106 1.0000