EPPLER E837 HYDROFOIL AIRFOIL (e837-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E837 HYDROFOIL AIRFOIL (e837-il) Reynolds number: 100,000 Max Cl/Cd: 43.19 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e837-il-100000.txt Download as CSV file: xf-e837-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E837 HYDROFOIL 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.7169 0.11447 0.10957 -0.0256 1.0000 0.0519
-14.500 -0.7252 0.10766 0.10272 -0.0284 1.0000 0.0509
-14.250 -0.7424 0.10024 0.09525 -0.0322 1.0000 0.0499
-14.000 -0.7713 0.09209 0.08698 -0.0368 1.0000 0.0493
-13.750 -0.7994 0.08500 0.07975 -0.0404 1.0000 0.0487
-13.500 -0.8251 0.07891 0.07348 -0.0429 1.0000 0.0481
-13.250 -0.8486 0.07352 0.06789 -0.0445 1.0000 0.0474
-13.000 -0.8723 0.06854 0.06268 -0.0452 1.0000 0.0470
-12.750 -0.8919 0.06422 0.05812 -0.0452 1.0000 0.0466
-12.500 -0.9095 0.06021 0.05384 -0.0445 1.0000 0.0462
-12.250 -0.9232 0.05661 0.04995 -0.0433 1.0000 0.0459
-12.000 -0.9329 0.05330 0.04636 -0.0417 1.0000 0.0459
-11.750 -0.9367 0.05042 0.04321 -0.0400 1.0000 0.0462
-11.500 -0.9377 0.04800 0.04054 -0.0381 1.0000 0.0477
-11.250 -0.9371 0.04571 0.03797 -0.0360 1.0000 0.0491
-11.000 -0.9328 0.04348 0.03540 -0.0338 1.0000 0.0504
-10.750 -0.9226 0.04139 0.03295 -0.0320 1.0000 0.0515
-10.500 -0.8691 0.03731 0.02890 -0.0352 1.0000 0.0560
-10.250 -0.8492 0.03568 0.02714 -0.0344 1.0000 0.0608
-10.000 -0.8185 0.03367 0.02519 -0.0344 1.0000 0.0676
-9.750 -0.7998 0.03225 0.02366 -0.0333 1.0000 0.0755
-9.500 -0.7838 0.03061 0.02223 -0.0321 1.0000 0.0866
-9.250 -0.7752 0.02898 0.02070 -0.0302 1.0000 0.1010
-9.000 -0.7756 0.02715 0.01919 -0.0276 1.0000 0.1200
-8.750 -0.7832 0.02532 0.01769 -0.0239 1.0000 0.1477
-8.500 -0.7995 0.02389 0.01663 -0.0186 1.0000 0.1783
-8.250 -0.8262 0.02350 0.01640 -0.0107 1.0000 0.1917
-8.000 -0.8546 0.02333 0.01630 -0.0025 1.0000 0.2015
-7.750 -0.8780 0.02265 0.01582 0.0046 1.0000 0.2292
-7.500 -0.8880 0.02131 0.01497 0.0091 0.9968 0.2947
-7.250 -0.8693 0.02013 0.01448 0.0089 0.9866 0.4081
-7.000 -0.8402 0.02026 0.01481 0.0083 0.9778 0.4841
-6.750 -0.8037 0.02109 0.01558 0.0071 0.9704 0.5345
-6.500 -0.7708 0.02210 0.01648 0.0069 0.9624 0.5634
-6.250 -0.7249 0.02345 0.01771 0.0049 0.9571 0.5863
-6.000 -0.6844 0.02475 0.01890 0.0040 0.9510 0.6039
-5.750 -0.6406 0.02593 0.01992 0.0025 0.9455 0.6189
-5.500 -0.5879 0.02712 0.02094 -0.0005 0.9421 0.6321
-5.250 -0.5520 0.02779 0.02146 -0.0013 0.9356 0.6443
-5.000 -0.5141 0.02817 0.02168 -0.0028 0.9299 0.6570
-4.750 -0.4510 0.02944 0.02282 -0.0068 0.9279 0.6629
-4.500 -0.4237 0.02949 0.02273 -0.0070 0.9207 0.6737
-4.250 -0.3917 0.02949 0.02261 -0.0079 0.9144 0.6846
-4.000 -0.3337 0.03011 0.02311 -0.0119 0.9119 0.6898
-3.750 -0.3296 0.02969 0.02260 -0.0090 0.9019 0.7017
-3.500 -0.2717 0.03025 0.02306 -0.0129 0.8988 0.7056
-3.250 -0.2695 0.02976 0.02250 -0.0099 0.8896 0.7171
-3.000 -0.2196 0.03012 0.02278 -0.0128 0.8855 0.7211
-2.750 -0.2174 0.02961 0.02220 -0.0099 0.8771 0.7321
-2.500 -0.1748 0.02990 0.02245 -0.0118 0.8718 0.7362
-2.250 -0.1677 0.02934 0.02180 -0.0096 0.8653 0.7469
-2.000 -0.1366 0.02965 0.02210 -0.0099 0.8583 0.7509
-1.750 -0.1295 0.02907 0.02145 -0.0076 0.8520 0.7615
-1.500 -0.1015 0.02941 0.02179 -0.0075 0.8449 0.7654
-1.250 -0.0777 0.02927 0.02161 -0.0073 0.8391 0.7722
-1.000 -0.0679 0.02917 0.02149 -0.0050 0.8320 0.7795
-0.750 -0.0439 0.02921 0.02152 -0.0047 0.8256 0.7853
-0.500 -0.0297 0.02889 0.02116 -0.0031 0.8203 0.7932
-0.250 -0.0144 0.02915 0.02145 -0.0016 0.8122 0.7986
0.000 -0.0001 0.02877 0.02103 0.0000 0.8072 0.8072
0.250 0.0142 0.02915 0.02144 0.0016 0.7986 0.8121
0.500 0.0298 0.02889 0.02116 0.0031 0.7932 0.8203
0.750 0.0441 0.02921 0.02152 0.0047 0.7853 0.8257
1.000 0.0677 0.02918 0.02149 0.0050 0.7796 0.8320
1.250 0.0778 0.02927 0.02161 0.0072 0.7723 0.8391
1.500 0.1015 0.02941 0.02179 0.0075 0.7654 0.8450
1.750 0.1294 0.02907 0.02145 0.0076 0.7615 0.8520
2.000 0.1363 0.02965 0.02210 0.0099 0.7509 0.8582
2.250 0.1677 0.02933 0.02179 0.0096 0.7469 0.8652
2.500 0.1750 0.02990 0.02244 0.0118 0.7362 0.8718
2.750 0.2171 0.02961 0.02220 0.0099 0.7321 0.8771
3.000 0.2196 0.03012 0.02278 0.0128 0.7211 0.8855
3.250 0.2696 0.02975 0.02249 0.0099 0.7171 0.8896
3.500 0.2718 0.03024 0.02305 0.0129 0.7056 0.8988
3.750 0.3295 0.02968 0.02258 0.0091 0.7017 0.9019
4.000 0.3338 0.03011 0.02311 0.0118 0.6898 0.9119
4.250 0.3918 0.02948 0.02259 0.0079 0.6846 0.9144
4.500 0.4240 0.02947 0.02271 0.0069 0.6737 0.9207
4.750 0.4513 0.02942 0.02280 0.0068 0.6629 0.9279
5.000 0.5141 0.02817 0.02168 0.0028 0.6570 0.9299
5.250 0.5521 0.02778 0.02145 0.0012 0.6443 0.9357
5.500 0.5881 0.02710 0.02093 0.0005 0.6320 0.9421
5.750 0.6405 0.02592 0.01991 -0.0025 0.6188 0.9455
6.000 0.6845 0.02475 0.01889 -0.0040 0.6040 0.9510
6.250 0.7248 0.02346 0.01772 -0.0049 0.5864 0.9571
6.500 0.7707 0.02210 0.01647 -0.0069 0.5635 0.9624
6.750 0.8037 0.02108 0.01558 -0.0070 0.5341 0.9704
7.000 0.8403 0.02025 0.01480 -0.0083 0.4838 0.9778
7.250 0.8694 0.02013 0.01447 -0.0089 0.4080 0.9866
7.500 0.8881 0.02132 0.01497 -0.0091 0.2939 0.9969
7.750 0.8777 0.02265 0.01582 -0.0046 0.2287 1.0000
8.000 0.8546 0.02332 0.01629 0.0025 0.2016 1.0000
8.250 0.8260 0.02349 0.01639 0.0107 0.1914 1.0000
8.500 0.7995 0.02389 0.01662 0.0186 0.1780 1.0000
8.750 0.7836 0.02531 0.01768 0.0239 0.1480 1.0000
9.000 0.7758 0.02714 0.01917 0.0275 0.1199 1.0000
9.250 0.7754 0.02898 0.02072 0.0302 0.1004 1.0000
9.500 0.7843 0.03061 0.02223 0.0321 0.0865 1.0000
9.750 0.8000 0.03226 0.02367 0.0333 0.0753 1.0000
10.000 0.8189 0.03366 0.02518 0.0344 0.0677 1.0000
10.250 0.8498 0.03566 0.02712 0.0344 0.0609 1.0000
10.500 0.8699 0.03731 0.02891 0.0351 0.0560 1.0000
10.750 0.9232 0.04140 0.03296 0.0319 0.0515 1.0000
11.000 0.9318 0.04340 0.03533 0.0339 0.0503 1.0000
11.250 0.9363 0.04557 0.03781 0.0360 0.0489 1.0000
11.500 0.9385 0.04804 0.04058 0.0380 0.0478 1.0000
11.750 0.9372 0.05047 0.04326 0.0399 0.0464 1.0000
12.000 0.9334 0.05330 0.04635 0.0416 0.0458 1.0000
12.250 0.9234 0.05666 0.05001 0.0432 0.0459 1.0000
12.500 0.9099 0.06025 0.05388 0.0444 0.0462 1.0000
12.750 0.8923 0.06425 0.05815 0.0451 0.0465 1.0000
13.000 0.8726 0.06860 0.06275 0.0451 0.0470 1.0000
13.250 0.8500 0.07350 0.06787 0.0444 0.0475 1.0000
13.500 0.8252 0.07901 0.07358 0.0427 0.0480 1.0000
13.750 0.7991 0.08519 0.07994 0.0402 0.0487 1.0000
14.000 0.7711 0.09224 0.08714 0.0365 0.0492 1.0000
14.250 0.7438 0.10025 0.09526 0.0321 0.0500 1.0000
14.500 0.7259 0.10778 0.10284 0.0282 0.0509 1.0000
14.750 0.7170 0.11465 0.10976 0.0253 0.0519 1.0000
15.000 0.4778 0.15096 0.14658 0.0060 0.1289 1.0000
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