E197 (13.49%) (e197-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E197 (13.49%) (e197-il) Reynolds number: 50,000 Max Cl/Cd: 25.89 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e197-il-50000-n5.txt Download as CSV file: xf-e197-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E197 (13.49%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4147 0.10053 0.09348 -0.0451 1.0000 0.0539
-10.500 -0.4203 0.09521 0.08825 -0.0476 1.0000 0.0535
-10.250 -0.4281 0.08950 0.08262 -0.0504 1.0000 0.0529
-10.000 -0.4413 0.08253 0.07574 -0.0543 1.0000 0.0522
-9.750 -0.4619 0.07508 0.06838 -0.0593 1.0000 0.0513
-9.500 -0.4913 0.06845 0.06179 -0.0636 1.0000 0.0505
-9.250 -0.5229 0.06415 0.05750 -0.0639 1.0000 0.0499
-9.000 -0.5489 0.06062 0.05391 -0.0623 1.0000 0.0495
-8.750 -0.5692 0.05748 0.05067 -0.0600 1.0000 0.0494
-8.500 -0.5862 0.05475 0.04779 -0.0571 1.0000 0.0492
-8.250 -0.6007 0.05239 0.04527 -0.0537 1.0000 0.0494
-8.000 -0.6127 0.05028 0.04297 -0.0502 1.0000 0.0495
-7.750 -0.5993 0.04670 0.03896 -0.0514 0.9911 0.0503
-7.500 -0.5740 0.04307 0.03480 -0.0540 0.9795 0.0516
-7.250 -0.5456 0.04009 0.03123 -0.0562 0.9688 0.0546
-7.000 -0.5165 0.03748 0.02809 -0.0579 0.9580 0.0579
-6.750 -0.4870 0.03555 0.02606 -0.0593 0.9478 0.0613
-6.500 -0.4532 0.03360 0.02383 -0.0609 0.9396 0.0652
-6.250 -0.4211 0.03186 0.02177 -0.0618 0.9304 0.0702
-6.000 -0.3914 0.03047 0.02034 -0.0629 0.9210 0.0785
-5.750 -0.3587 0.02905 0.01882 -0.0644 0.9134 0.0934
-5.500 -0.3338 0.02776 0.01756 -0.0647 0.9030 0.1141
-5.250 -0.3064 0.02648 0.01645 -0.0656 0.8945 0.1560
-5.000 -0.2807 0.02529 0.01555 -0.0662 0.8855 0.2148
-4.750 -0.2572 0.02438 0.01487 -0.0661 0.8762 0.2787
-4.500 -0.2293 0.02375 0.01451 -0.0664 0.8689 0.3546
-4.250 -0.2080 0.02358 0.01442 -0.0652 0.8590 0.4178
-4.000 -0.1811 0.02345 0.01425 -0.0647 0.8521 0.4735
-3.750 -0.1592 0.02343 0.01417 -0.0633 0.8430 0.5157
-3.500 -0.1337 0.02338 0.01403 -0.0624 0.8358 0.5544
-3.250 -0.1105 0.02337 0.01396 -0.0612 0.8279 0.5878
-3.000 -0.0853 0.02333 0.01383 -0.0602 0.8211 0.6197
-2.750 -0.0622 0.02334 0.01375 -0.0589 0.8133 0.6486
-2.500 -0.0356 0.02329 0.01362 -0.0582 0.8072 0.6772
-2.250 -0.0137 0.02334 0.01361 -0.0569 0.7994 0.7040
-2.000 0.0156 0.02325 0.01343 -0.0565 0.7944 0.7321
-1.750 0.0358 0.02338 0.01353 -0.0549 0.7861 0.7582
-1.500 0.0657 0.02335 0.01343 -0.0547 0.7809 0.7862
-1.250 0.0912 0.02348 0.01353 -0.0541 0.7737 0.8144
-1.000 0.1255 0.02352 0.01349 -0.0549 0.7680 0.8435
-0.750 0.1666 0.02356 0.01342 -0.0571 0.7633 0.8724
-0.500 0.2069 0.02376 0.01353 -0.0598 0.7563 0.9013
-0.250 0.2570 0.02376 0.01340 -0.0641 0.7517 0.9285
0.000 0.3049 0.02392 0.01344 -0.0687 0.7456 0.9562
0.250 0.3561 0.02399 0.01340 -0.0739 0.7397 0.9824
0.500 0.4009 0.02393 0.01321 -0.0778 0.7353 1.0000
0.750 0.4047 0.02448 0.01369 -0.0749 0.7266 1.0000
1.000 0.4247 0.02466 0.01375 -0.0740 0.7213 1.0000
1.250 0.4340 0.02528 0.01429 -0.0717 0.7133 1.0000
1.500 0.4550 0.02557 0.01451 -0.0708 0.7078 1.0000
1.750 0.4694 0.02615 0.01502 -0.0691 0.7007 1.0000
2.000 0.4886 0.02660 0.01542 -0.0680 0.6945 1.0000
2.250 0.5119 0.02694 0.01570 -0.0673 0.6894 1.0000
2.500 0.5246 0.02770 0.01647 -0.0655 0.6813 1.0000
2.750 0.5517 0.02794 0.01668 -0.0653 0.6769 1.0000
3.000 0.5621 0.02886 0.01761 -0.0634 0.6683 1.0000
3.250 0.5877 0.02919 0.01793 -0.0630 0.6633 1.0000
3.500 0.6007 0.03007 0.01886 -0.0614 0.6554 1.0000
3.750 0.6240 0.03051 0.01933 -0.0608 0.6495 1.0000
4.000 0.6407 0.03128 0.02013 -0.0595 0.6424 1.0000
4.250 0.6606 0.03189 0.02079 -0.0586 0.6355 1.0000
4.500 0.6815 0.03248 0.02146 -0.0578 0.6291 1.0000
4.750 0.6978 0.03326 0.02231 -0.0565 0.6210 1.0000
5.000 0.7185 0.03384 0.02297 -0.0556 0.6142 1.0000
5.250 0.7358 0.03456 0.02377 -0.0544 0.6060 1.0000
5.500 0.7507 0.03541 0.02471 -0.0529 0.5973 1.0000
5.750 0.7761 0.03567 0.02511 -0.0523 0.5904 1.0000
6.000 0.7857 0.03674 0.02628 -0.0504 0.5800 1.0000
6.250 0.8205 0.03641 0.02609 -0.0504 0.5742 1.0000
6.500 0.8269 0.03758 0.02737 -0.0481 0.5625 1.0000
6.750 0.8404 0.03833 0.02824 -0.0464 0.5520 1.0000
7.000 0.8772 0.03765 0.02777 -0.0463 0.5451 1.0000
7.250 0.8851 0.03858 0.02883 -0.0440 0.5326 1.0000
7.500 0.8956 0.03926 0.02965 -0.0418 0.5204 1.0000
7.750 0.9109 0.03957 0.03011 -0.0399 0.5085 1.0000
8.000 0.9341 0.03929 0.03005 -0.0384 0.4969 1.0000
8.250 0.9594 0.03874 0.02968 -0.0369 0.4844 1.0000
8.500 0.9736 0.03882 0.02993 -0.0346 0.4697 1.0000
8.750 0.9825 0.03929 0.03055 -0.0322 0.4534 1.0000
9.000 0.9938 0.03957 0.03099 -0.0300 0.4358 1.0000
9.250 1.0130 0.03913 0.03070 -0.0279 0.4167 1.0000
9.500 1.0188 0.03995 0.03167 -0.0257 0.3948 1.0000
9.750 1.0331 0.04000 0.03181 -0.0237 0.3700 1.0000
10.000 1.0426 0.04060 0.03242 -0.0216 0.3417 1.0000
10.250 1.0492 0.04157 0.03335 -0.0197 0.3109 1.0000
10.500 1.0533 0.04291 0.03454 -0.0178 0.2793 1.0000
10.750 1.0540 0.04475 0.03621 -0.0161 0.2499 1.0000
11.000 1.0523 0.04701 0.03830 -0.0146 0.2238 1.0000
11.250 1.0496 0.04951 0.04063 -0.0134 0.2013 1.0000
11.500 1.0469 0.05224 0.04330 -0.0125 0.1804 1.0000
11.750 1.0441 0.05505 0.04605 -0.0118 0.1623 1.0000
12.000 1.0419 0.05790 0.04880 -0.0111 0.1466 1.0000
12.250 1.0401 0.06081 0.05163 -0.0107 0.1323 1.0000
12.500 1.0390 0.06377 0.05456 -0.0103 0.1190 1.0000
12.750 1.0378 0.06684 0.05765 -0.0101 0.1067 1.0000
13.000 1.0371 0.06999 0.06085 -0.0100 0.0956 1.0000
13.250 1.0356 0.07334 0.06425 -0.0101 0.0854 1.0000
13.500 1.0348 0.07663 0.06754 -0.0103 0.0772 1.0000
13.750 1.0332 0.08012 0.07107 -0.0107 0.0696 1.0000
14.000 1.0334 0.08362 0.07472 -0.0111 0.0631 1.0000
14.250 1.0326 0.08715 0.07827 -0.0116 0.0578 1.0000
14.500 1.0325 0.09091 0.08220 -0.0122 0.0531 1.0000
14.750 1.0321 0.09481 0.08632 -0.0129 0.0496 1.0000
15.000 1.0324 0.09838 0.08995 -0.0138 0.0466 1.0000
15.250 1.0305 0.10266 0.09438 -0.0149 0.0443 1.0000
15.500 1.0226 0.10835 0.10041 -0.0170 0.0425 1.0000
15.750 1.0140 0.11429 0.10661 -0.0195 0.0413 1.0000
16.000 1.0030 0.12094 0.11350 -0.0226 0.0406 1.0000
16.250 0.9881 0.12878 0.12157 -0.0268 0.0403 1.0000
16.500 0.9674 0.13858 0.13159 -0.0323 0.0404 1.0000
16.750 0.9407 0.15118 0.14429 -0.0397 0.0413 1.0000
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Polar data table (+)
Polar graphs
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