E197 (13.49%) (e197-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E197 (13.49%) (e197-il) Reynolds number: 100,000 Max Cl/Cd: 52.51 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e197-il-100000.txt Download as CSV file: xf-e197-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3740 0.10928 0.10437 -0.0367 1.0000 0.1284
-10.250 -0.3693 0.10613 0.10126 -0.0373 1.0000 0.1328
-10.000 -0.4208 0.10296 0.09831 -0.0460 1.0000 0.1384
-9.750 -0.3809 0.09861 0.09390 -0.0409 1.0000 0.1411
-9.500 -0.3687 0.09600 0.09130 -0.0399 1.0000 0.1468
-9.250 -0.4160 0.09217 0.08770 -0.0469 1.0000 0.1526
-9.000 -0.3812 0.08889 0.08436 -0.0423 1.0000 0.1566
-8.750 -0.3779 0.08605 0.08158 -0.0418 1.0000 0.1616
-8.500 -0.4359 0.08270 0.07853 -0.0463 1.0000 0.1669
-8.000 -0.6070 0.06088 0.05641 -0.0480 0.9973 0.0812
-7.750 -0.5996 0.05015 0.04484 -0.0539 0.9859 0.0678
-7.500 -0.5769 0.04454 0.03880 -0.0572 0.9764 0.0655
-7.250 -0.5507 0.04001 0.03366 -0.0600 0.9673 0.0653
-7.000 -0.5205 0.03634 0.02937 -0.0623 0.9586 0.0662
-6.750 -0.4914 0.03328 0.02576 -0.0636 0.9493 0.0666
-6.500 -0.4530 0.03051 0.02243 -0.0660 0.9433 0.0678
-6.250 -0.4213 0.02842 0.01995 -0.0669 0.9344 0.0700
-6.000 -0.3802 0.02644 0.01801 -0.0699 0.9292 0.0766
-5.750 -0.3458 0.02496 0.01631 -0.0710 0.9214 0.0831
-5.500 -0.3091 0.02335 0.01475 -0.0727 0.9152 0.0949
-5.250 -0.2814 0.02194 0.01355 -0.0731 0.9072 0.1212
-5.000 -0.2543 0.02029 0.01234 -0.0735 0.8998 0.1868
-4.750 -0.2328 0.01932 0.01180 -0.0730 0.8908 0.2699
-4.500 -0.2059 0.01864 0.01161 -0.0731 0.8841 0.3770
-4.250 -0.1848 0.01861 0.01173 -0.0716 0.8750 0.4468
-4.000 -0.1551 0.01855 0.01169 -0.0715 0.8688 0.5024
-3.750 -0.1338 0.01869 0.01178 -0.0700 0.8602 0.5434
-3.500 -0.1053 0.01866 0.01178 -0.0694 0.8541 0.5805
-3.250 -0.0834 0.01878 0.01189 -0.0679 0.8463 0.6116
-3.000 -0.0570 0.01878 0.01186 -0.0671 0.8399 0.6413
-2.750 -0.0331 0.01884 0.01188 -0.0660 0.8332 0.6686
-2.500 -0.0098 0.01889 0.01192 -0.0647 0.8261 0.6944
-2.250 0.0198 0.01879 0.01179 -0.0641 0.8217 0.7201
-2.000 0.0363 0.01903 0.01203 -0.0621 0.8129 0.7441
-1.750 0.0641 0.01896 0.01194 -0.0613 0.8080 0.7692
-1.500 0.0828 0.01918 0.01219 -0.0595 0.8004 0.7935
-1.250 0.1084 0.01920 0.01219 -0.0585 0.7948 0.8205
-1.000 0.1359 0.01926 0.01223 -0.0577 0.7897 0.8484
-0.750 0.1619 0.01955 0.01254 -0.0572 0.7824 0.8768
-0.500 0.2069 0.01957 0.01248 -0.0596 0.7783 0.9037
-0.250 0.2548 0.01982 0.01267 -0.0634 0.7725 0.9294
0.000 0.3141 0.01995 0.01270 -0.0697 0.7669 0.9504
0.250 0.3785 0.01982 0.01244 -0.0767 0.7628 0.9693
0.500 0.4422 0.01986 0.01243 -0.0847 0.7567 0.9881
0.750 0.4852 0.01984 0.01234 -0.0890 0.7504 1.0000
1.000 0.4942 0.02001 0.01243 -0.0867 0.7451 1.0000
1.250 0.4960 0.02069 0.01310 -0.0836 0.7365 1.0000
1.500 0.5167 0.02082 0.01314 -0.0824 0.7319 1.0000
1.750 0.5226 0.02171 0.01402 -0.0797 0.7234 1.0000
2.000 0.5454 0.02193 0.01417 -0.0788 0.7183 1.0000
2.250 0.5581 0.02269 0.01492 -0.0769 0.7111 1.0000
2.500 0.5772 0.02316 0.01537 -0.0756 0.7047 1.0000
2.750 0.6076 0.02316 0.01532 -0.0755 0.7011 1.0000
3.000 0.6119 0.02442 0.01663 -0.0729 0.6913 1.0000
3.250 0.6422 0.02442 0.01662 -0.0728 0.6871 1.0000
3.500 0.6498 0.02564 0.01789 -0.0705 0.6778 1.0000
3.750 0.6792 0.02568 0.01793 -0.0703 0.6729 1.0000
4.000 0.6908 0.02672 0.01902 -0.0684 0.6642 1.0000
4.250 0.7189 0.02680 0.01914 -0.0681 0.6585 1.0000
4.500 0.7344 0.02764 0.02003 -0.0666 0.6501 1.0000
4.750 0.7624 0.02767 0.02010 -0.0661 0.6437 1.0000
5.000 0.7795 0.02838 0.02088 -0.0647 0.6351 1.0000
5.250 0.8101 0.02819 0.02076 -0.0644 0.6285 1.0000
5.500 0.8264 0.02887 0.02152 -0.0629 0.6189 1.0000
5.750 0.8638 0.02817 0.02087 -0.0631 0.6129 1.0000
6.000 0.8789 0.02882 0.02164 -0.0613 0.6023 1.0000
6.250 0.9242 0.02750 0.02036 -0.0621 0.5967 1.0000
6.500 0.9406 0.02788 0.02088 -0.0602 0.5849 1.0000
6.750 0.9662 0.02765 0.02074 -0.0591 0.5745 1.0000
7.000 1.0114 0.02610 0.01923 -0.0598 0.5664 1.0000
7.250 1.0336 0.02585 0.01911 -0.0583 0.5533 1.0000
7.500 1.0591 0.02532 0.01870 -0.0570 0.5399 1.0000
7.750 1.0864 0.02460 0.01809 -0.0558 0.5254 1.0000
8.000 1.1141 0.02379 0.01736 -0.0546 0.5095 1.0000
8.250 1.1387 0.02310 0.01674 -0.0531 0.4912 1.0000
8.500 1.1547 0.02281 0.01660 -0.0505 0.4689 1.0000
8.750 1.1708 0.02252 0.01639 -0.0479 0.4430 1.0000
9.000 1.1819 0.02251 0.01640 -0.0447 0.4109 1.0000
9.250 1.1873 0.02285 0.01665 -0.0409 0.3720 1.0000
9.500 1.1843 0.02366 0.01726 -0.0362 0.3277 1.0000
9.750 1.1740 0.02496 0.01825 -0.0309 0.2864 1.0000
10.000 1.1624 0.02674 0.01972 -0.0263 0.2492 1.0000
10.250 1.1509 0.02888 0.02155 -0.0224 0.2175 1.0000
10.500 1.1410 0.03122 0.02364 -0.0194 0.1891 1.0000
10.750 1.1334 0.03364 0.02591 -0.0170 0.1635 1.0000
11.000 1.1278 0.03612 0.02823 -0.0150 0.1415 1.0000
11.250 1.1227 0.03868 0.03065 -0.0134 0.1226 1.0000
11.500 1.1192 0.04129 0.03310 -0.0119 0.1058 1.0000
11.750 1.1177 0.04386 0.03564 -0.0106 0.0905 1.0000
12.000 1.1166 0.04653 0.03825 -0.0093 0.0767 1.0000
12.250 1.1220 0.04887 0.04050 -0.0079 0.0662 1.0000
12.500 1.1328 0.05090 0.04240 -0.0066 0.0583 1.0000
12.750 1.1433 0.05313 0.04481 -0.0055 0.0523 1.0000
13.000 1.1679 0.05507 0.04655 -0.0043 0.0467 1.0000
13.250 1.1794 0.05753 0.04933 -0.0033 0.0449 1.0000
13.500 1.1905 0.06036 0.05245 -0.0024 0.0431 1.0000
13.750 1.1981 0.06347 0.05584 -0.0017 0.0420 1.0000
14.000 1.2005 0.06691 0.05953 -0.0011 0.0411 1.0000
14.250 1.1989 0.07040 0.06324 -0.0008 0.0402 1.0000
14.500 1.1935 0.07432 0.06740 -0.0008 0.0398 1.0000
14.750 1.1843 0.07863 0.07195 -0.0011 0.0395 1.0000
15.000 1.1759 0.08285 0.07633 -0.0017 0.0387 1.0000
15.250 1.1613 0.08785 0.08156 -0.0028 0.0386 1.0000
15.500 1.1261 0.09555 0.08972 -0.0056 0.0400 1.0000
15.750 1.0915 0.10395 0.09845 -0.0097 0.0407 1.0000
16.000 1.0520 0.11437 0.10919 -0.0155 0.0421 1.0000
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Polar data table (+)
Polar graphs
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