EPPLER E1212 AIRFOIL (e1212-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E1212 AIRFOIL (e1212-il) Reynolds number: 100,000 Max Cl/Cd: 32.08 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1212-il-100000.txt Download as CSV file: xf-e1212-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E1212 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.3620 0.14384 0.13831 -0.0144 1.0000 0.1568
-13.000 -0.3338 0.14060 0.13506 -0.0129 1.0000 0.1626
-12.750 -0.3587 0.13889 0.13339 -0.0167 1.0000 0.1687
-12.500 -0.3328 0.13391 0.12840 -0.0157 1.0000 0.1718
-12.250 -0.3188 0.13129 0.12579 -0.0156 1.0000 0.1785
-12.000 -0.3597 0.12962 0.12419 -0.0206 1.0000 0.1831
-11.750 -0.3141 0.12462 0.11916 -0.0177 1.0000 0.1874
-11.500 -0.3086 0.12228 0.11684 -0.0183 1.0000 0.1954
-11.250 -0.3594 0.12017 0.11481 -0.0240 1.0000 0.1985
-11.000 -0.2979 0.11565 0.11024 -0.0196 1.0000 0.2037
-10.750 -0.3008 0.11356 0.10818 -0.0207 1.0000 0.2124
-10.500 -0.3560 0.11093 0.10566 -0.0264 1.0000 0.2148
-10.250 -0.2847 0.10695 0.10161 -0.0212 1.0000 0.2203
-10.000 -0.2919 0.10505 0.09976 -0.0224 1.0000 0.2298
-9.750 -0.3265 0.10146 0.09627 -0.0258 1.0000 0.2327
-9.500 -0.2727 0.09867 0.09344 -0.0223 1.0000 0.2379
-9.250 -0.2748 0.09671 0.09152 -0.0228 1.0000 0.2469
-9.000 -0.3489 0.09388 0.08889 -0.0278 1.0000 0.2501
-8.750 -0.2643 0.09085 0.08577 -0.0228 1.0000 0.2560
-8.500 -0.2628 0.08900 0.08398 -0.0226 1.0000 0.2646
-8.250 -0.3714 0.08173 0.07702 -0.0281 1.0000 0.2505
-8.000 -0.3655 0.07948 0.07489 -0.0256 1.0000 0.2512
-7.750 -0.3393 0.07645 0.07188 -0.0277 0.9887 0.2525
-7.500 -0.4428 0.04467 0.03924 -0.0632 0.9387 0.2284
-7.250 -0.4088 0.04129 0.03562 -0.0680 0.9216 0.2356
-7.000 -0.3623 0.04084 0.03515 -0.0705 0.9041 0.2419
-6.750 -0.3542 0.03562 0.02913 -0.0740 0.8827 0.2506
-6.500 -0.3154 0.03565 0.02933 -0.0742 0.8628 0.2548
-6.250 -0.2885 0.03499 0.02855 -0.0739 0.8425 0.2601
-6.000 -0.2744 0.03287 0.02597 -0.0737 0.8232 0.2669
-5.750 -0.2549 0.03155 0.02442 -0.0729 0.8050 0.2717
-5.500 -0.2292 0.03129 0.02418 -0.0719 0.7876 0.2760
-5.250 -0.2071 0.03054 0.02323 -0.0710 0.7720 0.2816
-5.000 -0.1878 0.02931 0.02149 -0.0704 0.7578 0.2880
-4.750 -0.1650 0.02852 0.02069 -0.0695 0.7419 0.2922
-4.500 -0.1402 0.02817 0.02032 -0.0686 0.7278 0.2970
-4.250 -0.1159 0.02757 0.01946 -0.0679 0.7155 0.3029
-4.000 -0.0938 0.02688 0.01843 -0.0673 0.7011 0.3087
-3.750 -0.0687 0.02628 0.01784 -0.0666 0.6892 0.3133
-3.500 -0.0433 0.02594 0.01743 -0.0658 0.6766 0.3186
-3.250 -0.0185 0.02553 0.01684 -0.0653 0.6644 0.3245
-3.000 0.0072 0.02502 0.01604 -0.0648 0.6537 0.3303
-2.750 0.0322 0.02470 0.01578 -0.0641 0.6415 0.3354
-2.500 0.0591 0.02440 0.01532 -0.0636 0.6318 0.3415
-2.250 0.0842 0.02418 0.01496 -0.0631 0.6197 0.3480
-2.000 0.1113 0.02379 0.01444 -0.0626 0.6108 0.3538
-1.750 0.1363 0.02364 0.01435 -0.0620 0.5991 0.3599
-1.500 0.1640 0.02343 0.01392 -0.0616 0.5905 0.3673
-1.250 0.1892 0.02326 0.01376 -0.0611 0.5795 0.3740
-1.000 0.2165 0.02307 0.01352 -0.0606 0.5710 0.3813
-0.750 0.2423 0.02306 0.01344 -0.0601 0.5609 0.3894
-0.500 0.2692 0.02284 0.01320 -0.0597 0.5521 0.3973
-0.250 0.2955 0.02285 0.01320 -0.0592 0.5436 0.4068
0.000 0.3217 0.02277 0.01311 -0.0587 0.5344 0.4167
0.250 0.3500 0.02269 0.01294 -0.0583 0.5275 0.4277
0.500 0.3739 0.02274 0.01313 -0.0577 0.5175 0.4395
0.750 0.4017 0.02268 0.01299 -0.0573 0.5104 0.4549
1.000 0.4263 0.02277 0.01323 -0.0566 0.5022 0.4704
1.250 0.4520 0.02273 0.01329 -0.0559 0.4941 0.4895
1.500 0.4804 0.02266 0.01318 -0.0556 0.4882 0.5157
1.750 0.5020 0.02282 0.01367 -0.0545 0.4793 0.5463
2.000 0.5271 0.02268 0.01372 -0.0536 0.4726 0.5918
2.250 0.5511 0.02259 0.01389 -0.0522 0.4666 0.6633
2.500 0.5677 0.02251 0.01442 -0.0494 0.4588 0.7775
2.750 0.6463 0.02226 0.01423 -0.0574 0.4501 0.9977
3.000 0.6652 0.02289 0.01482 -0.0565 0.4428 1.0000
3.250 0.6875 0.02329 0.01510 -0.0556 0.4361 1.0000
3.500 0.7148 0.02355 0.01512 -0.0553 0.4310 1.0000
3.750 0.7338 0.02430 0.01591 -0.0541 0.4244 1.0000
4.000 0.7558 0.02483 0.01640 -0.0532 0.4179 1.0000
4.250 0.7832 0.02510 0.01648 -0.0529 0.4128 1.0000
4.500 0.8043 0.02583 0.01722 -0.0519 0.4070 1.0000
4.750 0.8239 0.02655 0.01798 -0.0509 0.4005 1.0000
5.000 0.8499 0.02694 0.01827 -0.0504 0.3956 1.0000
5.250 0.8788 0.02739 0.01852 -0.0503 0.3915 1.0000
5.500 0.8905 0.02858 0.01995 -0.0485 0.3847 1.0000
5.750 0.9133 0.02914 0.02049 -0.0478 0.3793 1.0000
6.000 0.9422 0.02942 0.02062 -0.0476 0.3751 1.0000
6.250 0.9594 0.03056 0.02183 -0.0465 0.3703 1.0000
6.500 0.9717 0.03188 0.02331 -0.0449 0.3647 1.0000
6.750 0.9951 0.03247 0.02387 -0.0442 0.3601 1.0000
7.000 1.0260 0.03270 0.02395 -0.0443 0.3564 1.0000
7.250 1.0345 0.03435 0.02577 -0.0424 0.3515 1.0000
7.500 1.0401 0.03610 0.02770 -0.0404 0.3462 1.0000
7.750 1.0611 0.03691 0.02851 -0.0397 0.3423 1.0000
8.000 1.0915 0.03721 0.02870 -0.0397 0.3391 1.0000
8.250 1.1047 0.03875 0.03031 -0.0384 0.3354 1.0000
8.500 1.0599 0.04359 0.03559 -0.0331 0.3296 1.0000
8.750 1.0541 0.04597 0.03806 -0.0307 0.3254 1.0000
9.000 1.1010 0.04515 0.03712 -0.0316 0.3226 1.0000
9.250 1.1481 0.04465 0.03647 -0.0327 0.3202 1.0000
10.000 0.5609 0.12501 0.11793 -0.0541 0.3458 1.0000
10.250 0.5781 0.12733 0.12024 -0.0542 0.3416 1.0000
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Polar data table (+)
Polar graphs
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