EPPLER 664 AIRFOIL (e664-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
Details | Polar file |
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Airfoil: EPPLER 664 AIRFOIL (e664-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.94 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e664-il-1000000.txt Download as CSV file: xf-e664-il-1000000.csv |
XFOIL Version 6.96 Calculated polar for: EPPLER 664 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -12.750 -0.1859 0.08427 0.08180 -0.1029 0.8012 0.0166 -12.500 -0.1971 0.07764 0.07515 -0.1057 0.7990 0.0169 -11.750 -0.5371 0.03443 0.03044 -0.1238 0.8026 0.0116 -11.500 -0.5519 0.03169 0.02744 -0.1201 0.7976 0.0113 -11.250 -0.5580 0.02949 0.02504 -0.1170 0.7937 0.0111 -11.000 -0.5617 0.02742 0.02272 -0.1137 0.7897 0.0110 -10.750 -0.5591 0.02565 0.02073 -0.1109 0.7862 0.0109 -10.500 -0.5527 0.02374 0.01855 -0.1085 0.7827 0.0109 -10.250 -0.5402 0.02220 0.01682 -0.1068 0.7803 0.0107 -10.000 -0.5247 0.02099 0.01545 -0.1054 0.7778 0.0109 -9.750 -0.5071 0.02000 0.01434 -0.1043 0.7753 0.0110 -9.500 -0.4871 0.01901 0.01323 -0.1035 0.7728 0.0110 -9.250 -0.4665 0.01815 0.01228 -0.1027 0.7706 0.0111 -9.000 -0.4461 0.01748 0.01152 -0.1019 0.7683 0.0114 -8.750 -0.4254 0.01693 0.01087 -0.1011 0.7657 0.0116 -8.500 -0.4044 0.01623 0.01012 -0.1003 0.7643 0.0117 -8.250 -0.3840 0.01564 0.00948 -0.0994 0.7626 0.0118 -8.000 -0.3636 0.01525 0.00906 -0.0985 0.7608 0.0121 -7.750 -0.3433 0.01483 0.00859 -0.0975 0.7590 0.0122 -7.500 -0.3240 0.01433 0.00805 -0.0964 0.7572 0.0123 -7.250 -0.3095 0.01360 0.00727 -0.0944 0.7552 0.0125 -7.000 -0.2955 0.01307 0.00669 -0.0923 0.7532 0.0129 -6.750 -0.2771 0.01273 0.00630 -0.0910 0.7512 0.0131 -6.500 -0.2567 0.01239 0.00594 -0.0900 0.7493 0.0137 -6.250 -0.2353 0.01209 0.00563 -0.0891 0.7481 0.0142 -6.000 -0.2133 0.01181 0.00534 -0.0883 0.7468 0.0148 -5.750 -0.1907 0.01156 0.00506 -0.0877 0.7453 0.0153 -5.500 -0.1689 0.01124 0.00472 -0.0868 0.7436 0.0160 -5.250 -0.1464 0.01096 0.00442 -0.0861 0.7420 0.0169 -5.000 -0.1228 0.01073 0.00418 -0.0856 0.7405 0.0182 -4.750 -0.0987 0.01052 0.00396 -0.0852 0.7390 0.0201 -4.500 -0.0756 0.01025 0.00373 -0.0846 0.7375 0.0288 -4.250 -0.0551 0.00982 0.00351 -0.0837 0.7357 0.0722 -4.000 -0.0324 0.00952 0.00336 -0.0832 0.7336 0.1133 -3.750 -0.0106 0.00913 0.00320 -0.0825 0.7323 0.1664 -3.500 0.0105 0.00865 0.00301 -0.0819 0.7309 0.2425 -3.250 0.0310 0.00804 0.00280 -0.0812 0.7292 0.3453 -3.000 0.0507 0.00714 0.00246 -0.0806 0.7273 0.5033 -2.750 0.0731 0.00630 0.00231 -0.0804 0.7255 0.6941 -2.500 0.1021 0.00639 0.00245 -0.0806 0.7239 0.7289 -2.250 0.1316 0.00650 0.00253 -0.0810 0.7224 0.7427 -2.000 0.1612 0.00665 0.00265 -0.0814 0.7208 0.7526 -1.750 0.1904 0.00690 0.00288 -0.0817 0.7191 0.7605 -1.500 0.2200 0.00710 0.00305 -0.0821 0.7171 0.7650 -1.250 0.2493 0.00720 0.00312 -0.0825 0.7159 0.7697 -1.000 0.2770 0.00742 0.00339 -0.0823 0.7142 0.7749 -0.750 0.3048 0.00771 0.00370 -0.0821 0.7120 0.7804 -0.500 0.3339 0.00798 0.00395 -0.0823 0.7092 0.7864 -0.250 0.3609 0.00808 0.00407 -0.0820 0.7068 0.7894 0.000 0.3892 0.00817 0.00414 -0.0821 0.7046 0.7909 0.250 0.4186 0.00821 0.00414 -0.0827 0.7021 0.7917 0.500 0.4472 0.00820 0.00413 -0.0831 0.6998 0.7927 0.750 0.4755 0.00816 0.00410 -0.0834 0.6973 0.7937 1.000 0.5042 0.00812 0.00406 -0.0838 0.6946 0.7946 1.250 0.5331 0.00808 0.00401 -0.0843 0.6918 0.7954 1.500 0.5620 0.00806 0.00396 -0.0848 0.6891 0.7964 1.750 0.5915 0.00809 0.00395 -0.0854 0.6857 0.7975 2.000 0.6195 0.00803 0.00392 -0.0857 0.6827 0.7985 2.250 0.6479 0.00798 0.00389 -0.0861 0.6791 0.7993 2.500 0.6764 0.00794 0.00384 -0.0865 0.6754 0.8002 2.750 0.7052 0.00793 0.00380 -0.0870 0.6715 0.8009 3.000 0.7335 0.00792 0.00381 -0.0874 0.6675 0.8015 3.250 0.7612 0.00788 0.00379 -0.0876 0.6624 0.8022 3.500 0.7884 0.00780 0.00371 -0.0877 0.6571 0.8032 3.750 0.8155 0.00777 0.00370 -0.0878 0.6517 0.8039 4.000 0.8424 0.00774 0.00370 -0.0879 0.6448 0.8045 4.250 0.8688 0.00775 0.00370 -0.0878 0.6374 0.8052 4.500 0.8950 0.00775 0.00372 -0.0877 0.6278 0.8058 4.750 0.9205 0.00779 0.00376 -0.0875 0.6163 0.8065 5.000 0.9445 0.00786 0.00380 -0.0870 0.6012 0.8072 5.250 0.9663 0.00799 0.00388 -0.0860 0.5816 0.8080 5.500 0.9859 0.00820 0.00400 -0.0846 0.5576 0.8088 6.000 1.0204 0.00877 0.00439 -0.0810 0.5079 0.8109 6.250 1.0351 0.00910 0.00462 -0.0787 0.4822 0.8120 6.500 1.0431 0.00947 0.00487 -0.0751 0.4517 0.8131 6.750 1.0487 0.00995 0.00520 -0.0711 0.4190 0.8142 7.000 1.0539 0.01056 0.00564 -0.0673 0.3839 0.8153 7.250 1.0620 0.01113 0.00608 -0.0641 0.3558 0.8162 7.500 1.0714 0.01169 0.00654 -0.0612 0.3312 0.8170 7.750 1.0815 0.01226 0.00701 -0.0586 0.3090 0.8178 8.000 1.0893 0.01287 0.00752 -0.0557 0.2842 0.8190 8.250 1.0973 0.01355 0.00811 -0.0529 0.2609 0.8201 8.500 1.1053 0.01430 0.00877 -0.0502 0.2389 0.8212 8.750 1.1134 0.01509 0.00948 -0.0477 0.2174 0.8222 9.000 1.1221 0.01592 0.01022 -0.0454 0.1966 0.8231 9.250 1.1295 0.01685 0.01105 -0.0431 0.1756 0.8240 9.500 1.1390 0.01773 0.01185 -0.0411 0.1571 0.8250 9.750 1.1489 0.01862 0.01267 -0.0393 0.1403 0.8259 10.000 1.1577 0.01961 0.01357 -0.0373 0.1228 0.8268 10.250 1.1657 0.02067 0.01454 -0.0354 0.1057 0.8277 10.500 1.1763 0.02162 0.01544 -0.0339 0.0931 0.8286 10.750 1.1864 0.02262 0.01638 -0.0324 0.0811 0.8294 11.000 1.1958 0.02369 0.01740 -0.0308 0.0689 0.8302 11.250 1.2055 0.02479 0.01844 -0.0294 0.0579 0.8311 11.500 1.2138 0.02598 0.01958 -0.0279 0.0469 0.8318 11.750 1.2216 0.02726 0.02080 -0.0264 0.0362 0.8325 12.000 1.2242 0.02892 0.02235 -0.0245 0.0222 0.8332 12.250 1.2304 0.03035 0.02375 -0.0230 0.0152 0.8342 12.500 1.2396 0.03162 0.02503 -0.0219 0.0129 0.8350 12.750 1.2496 0.03287 0.02633 -0.0208 0.0117 0.8359 13.000 1.2596 0.03415 0.02766 -0.0198 0.0108 0.8366 13.250 1.2700 0.03543 0.02899 -0.0190 0.0104 0.8374 13.500 1.2774 0.03697 0.03059 -0.0179 0.0098 0.8382 13.750 1.2848 0.03858 0.03226 -0.0170 0.0094 0.8390 14.000 1.2939 0.04007 0.03382 -0.0163 0.0092 0.8398 14.250 1.3030 0.04160 0.03542 -0.0156 0.0090 0.8406 14.500 1.3105 0.04331 0.03720 -0.0149 0.0087 0.8414 14.750 1.3181 0.04505 0.03901 -0.0143 0.0086 0.8421 15.000 1.3241 0.04699 0.04102 -0.0138 0.0084 0.8430 15.250 1.3298 0.04902 0.04311 -0.0133 0.0082 0.8439 15.500 1.3343 0.05122 0.04539 -0.0128 0.0080 0.8447 15.750 1.3381 0.05353 0.04777 -0.0125 0.0079 0.8455 16.000 1.3402 0.05611 0.05043 -0.0123 0.0076 0.8462 16.250 1.3384 0.05922 0.05363 -0.0121 0.0075 0.8468 16.500 1.3373 0.06236 0.05687 -0.0121 0.0074 0.8473 16.750 1.3279 0.06661 0.06124 -0.0123 0.0072 0.8477 17.000 1.3289 0.06968 0.06440 -0.0127 0.0072 0.8484 17.250 1.3293 0.07291 0.06772 -0.0132 0.0071 0.8493 17.500 1.3309 0.07606 0.07096 -0.0139 0.0070 0.8502 17.750 1.3293 0.07972 0.07473 -0.0147 0.0070 0.8509 18.000 1.3269 0.08354 0.07865 -0.0157 0.0069 0.8516 18.250 1.3242 0.08751 0.08272 -0.0169 0.0068 0.8523 18.500 1.3205 0.09171 0.08703 -0.0182 0.0068 0.8529 18.750 1.3169 0.09599 0.09142 -0.0198 0.0067 0.8536 19.000 1.3130 0.10040 0.09593 -0.0215 0.0067 0.8542 19.250 1.3066 0.10522 0.10086 -0.0234 0.0066 0.8548 |
Polar data table (+)
Polar graphs
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