EPPLER 266 AIRFOIL (e266-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 266 AIRFOIL (e266-il) Reynolds number: 100,000 Max Cl/Cd: 23.49 at α=12° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e266-il-100000-n5.txt Download as CSV file: xf-e266-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 266 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.2850 0.09453 0.08937 -0.0877 0.8560 0.0281
-11.750 -0.2821 0.08910 0.08384 -0.0916 0.8386 0.0277
-11.500 -0.2864 0.08246 0.07709 -0.0961 0.8253 0.0273
-11.250 -0.3036 0.07458 0.06909 -0.1016 0.8149 0.0268
-11.000 -0.3253 0.06834 0.06268 -0.1052 0.8050 0.0264
-10.750 -0.3469 0.06347 0.05762 -0.1068 0.7966 0.0261
-10.500 -0.3675 0.05944 0.05337 -0.1067 0.7887 0.0258
-10.250 -0.3873 0.05587 0.04955 -0.1055 0.7821 0.0255
-10.000 -0.4042 0.05281 0.04626 -0.1032 0.7753 0.0253
-9.750 -0.4196 0.05000 0.04317 -0.1001 0.7696 0.0251
-9.500 -0.4311 0.04766 0.04054 -0.0965 0.7644 0.0249
-9.250 -0.4365 0.04512 0.03768 -0.0935 0.7591 0.0248
-9.000 -0.4366 0.04261 0.03479 -0.0907 0.7545 0.0248
-8.750 -0.4313 0.04029 0.03208 -0.0884 0.7507 0.0248
-8.500 -0.4223 0.03818 0.02964 -0.0864 0.7462 0.0248
-8.250 -0.4091 0.03617 0.02729 -0.0848 0.7422 0.0250
-8.000 -0.3919 0.03432 0.02510 -0.0836 0.7388 0.0253
-7.750 -0.3710 0.03263 0.02310 -0.0829 0.7359 0.0256
-7.500 -0.3482 0.03114 0.02135 -0.0824 0.7329 0.0263
-7.250 -0.3241 0.02987 0.01986 -0.0820 0.7296 0.0273
-7.000 -0.2990 0.02865 0.01847 -0.0819 0.7265 0.0288
-6.750 -0.2744 0.02766 0.01743 -0.0817 0.7236 0.0300
-6.500 -0.2490 0.02667 0.01634 -0.0815 0.7209 0.0311
-6.250 -0.2250 0.02579 0.01534 -0.0810 0.7186 0.0322
-6.000 -0.2047 0.02507 0.01454 -0.0800 0.7155 0.0335
-5.750 -0.1867 0.02439 0.01382 -0.0786 0.7125 0.0350
-5.500 -0.1687 0.02384 0.01324 -0.0773 0.7099 0.0373
-5.250 -0.1496 0.02338 0.01268 -0.0761 0.7075 0.0415
-5.000 -0.1313 0.02283 0.01212 -0.0748 0.7053 0.0475
-4.750 -0.1123 0.02226 0.01154 -0.0734 0.7034 0.0581
-4.500 -0.0947 0.02156 0.01106 -0.0719 0.7013 0.0973
-4.250 -0.0820 0.02076 0.01086 -0.0699 0.6985 0.1991
-4.000 -0.0819 0.01960 0.01069 -0.0659 0.6956 0.3838
-3.750 -0.0478 0.02106 0.01360 -0.0621 0.6935 0.7053
-3.500 -0.0390 0.02162 0.01403 -0.0582 0.6913 0.7412
-3.250 -0.0099 0.02258 0.01480 -0.0570 0.6895 0.7621
-3.000 0.0196 0.02338 0.01541 -0.0561 0.6878 0.7807
-2.750 0.0533 0.02409 0.01594 -0.0560 0.6862 0.7968
-2.500 0.0808 0.02453 0.01623 -0.0555 0.6840 0.8087
-2.250 0.0937 0.02477 0.01641 -0.0529 0.6811 0.8205
-2.000 0.1287 0.02499 0.01651 -0.0541 0.6788 0.8254
-1.750 0.1375 0.02509 0.01654 -0.0510 0.6765 0.8357
-1.500 0.1719 0.02518 0.01650 -0.0524 0.6746 0.8391
-1.250 0.1997 0.02522 0.01643 -0.0526 0.6727 0.8439
-1.000 0.2113 0.02521 0.01632 -0.0500 0.6708 0.8516
-0.750 0.2444 0.02520 0.01619 -0.0512 0.6693 0.8543
-0.500 0.2631 0.02542 0.01639 -0.0501 0.6666 0.8589
-0.250 0.2634 0.02562 0.01662 -0.0458 0.6637 0.8664
0.000 0.2890 0.02576 0.01671 -0.0459 0.6610 0.8691
0.250 0.3122 0.02584 0.01675 -0.0455 0.6586 0.8725
0.500 0.3294 0.02590 0.01676 -0.0440 0.6565 0.8770
0.750 0.3413 0.02593 0.01674 -0.0415 0.6547 0.8819
1.000 0.3713 0.02595 0.01669 -0.0423 0.6533 0.8838
1.250 0.3811 0.02638 0.01718 -0.0399 0.6496 0.8876
1.500 0.3840 0.02677 0.01762 -0.0362 0.6457 0.8925
1.750 0.3862 0.02699 0.01784 -0.0322 0.6426 0.8974
2.000 0.4113 0.02709 0.01792 -0.0323 0.6404 0.8995
2.250 0.4376 0.02712 0.01792 -0.0324 0.6385 0.9015
2.500 0.4640 0.02714 0.01792 -0.0326 0.6370 0.9036
2.750 0.4246 0.02831 0.01922 -0.0223 0.6293 0.9118
3.000 0.4418 0.02858 0.01951 -0.0212 0.6260 0.9140
3.250 0.4664 0.02868 0.01960 -0.0211 0.6237 0.9161
3.500 0.4940 0.02868 0.01959 -0.0214 0.6220 0.9183
3.750 0.5232 0.02862 0.01954 -0.0220 0.6205 0.9201
4.250 0.5031 0.03044 0.02150 -0.0120 0.6072 0.9298
4.500 0.5351 0.03035 0.02142 -0.0129 0.6056 0.9316
4.750 0.5681 0.03021 0.02130 -0.0140 0.6042 0.9332
5.250 0.5559 0.03221 0.02343 -0.0060 0.5898 0.9425
5.500 0.5881 0.03207 0.02332 -0.0069 0.5880 0.9445
6.000 0.6033 0.03420 0.02562 -0.0042 0.5737 0.9526
6.250 0.6409 0.03374 0.02522 -0.0056 0.5726 0.9539
6.750 0.6623 0.03625 0.02793 -0.0050 0.5564 0.9615
7.250 0.6962 0.03857 0.03047 -0.0064 0.5400 0.9688
7.750 0.7499 0.03918 0.03132 -0.0085 0.5285 0.9773
8.250 0.7863 0.04035 0.03269 -0.0087 0.5139 1.0000
8.500 0.7801 0.04202 0.03441 -0.0063 0.5017 1.0000
8.750 0.8121 0.04105 0.03356 -0.0062 0.4991 1.0000
9.250 0.8384 0.04208 0.03476 -0.0044 0.4822 1.0000
9.500 0.8478 0.04298 0.03574 -0.0035 0.4715 1.0000
10.000 0.8888 0.04295 0.03594 -0.0025 0.4555 1.0000
10.250 0.8979 0.04403 0.03711 -0.0018 0.4429 1.0000
10.750 0.9366 0.04432 0.03761 -0.0009 0.4203 1.0000
11.000 0.9638 0.04369 0.03707 -0.0006 0.4083 1.0000
11.250 0.9838 0.04378 0.03722 -0.0001 0.3927 1.0000
11.500 1.0021 0.04402 0.03752 0.0005 0.3745 1.0000
11.750 1.0224 0.04406 0.03754 0.0011 0.3545 1.0000
12.000 1.0404 0.04429 0.03770 0.0018 0.3320 1.0000
12.250 1.0500 0.04541 0.03874 0.0027 0.3077 1.0000
12.500 1.0560 0.04691 0.04014 0.0035 0.2821 1.0000
12.750 1.0586 0.04881 0.04190 0.0044 0.2564 1.0000
13.000 1.0587 0.05107 0.04405 0.0051 0.2313 1.0000
13.250 1.0572 0.05361 0.04647 0.0057 0.2063 1.0000
13.500 1.0543 0.05639 0.04909 0.0061 0.1820 1.0000
13.750 1.0512 0.05933 0.05190 0.0064 0.1581 1.0000
14.000 1.0490 0.06229 0.05474 0.0065 0.1366 1.0000
14.250 1.0474 0.06527 0.05763 0.0065 0.1172 1.0000
14.500 1.0476 0.06815 0.06047 0.0064 0.1026 1.0000
14.750 1.0467 0.07121 0.06351 0.0062 0.0876 1.0000
15.000 1.0467 0.07425 0.06655 0.0059 0.0760 1.0000
15.250 1.0449 0.07760 0.06989 0.0055 0.0630 1.0000
15.500 1.0432 0.08101 0.07330 0.0050 0.0545 1.0000
15.750 1.0391 0.08480 0.07707 0.0044 0.0461 1.0000
16.000 1.0370 0.08843 0.08077 0.0037 0.0402 1.0000
16.250 1.0335 0.09231 0.08469 0.0028 0.0363 1.0000
16.500 1.0311 0.09613 0.08860 0.0019 0.0330 1.0000
16.750 1.0269 0.10026 0.09276 0.0007 0.0308 1.0000
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Polar data table (+)
Polar graphs
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