EH 2.0/12 (eh2012-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 2.0/12 (eh2012-il) Reynolds number: 200,000 Max Cl/Cd: 61.77 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh2012-il-200000.txt Download as CSV file: xf-eh2012-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.0/12
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6464 0.05641 0.05260 -0.0289 1.0000 0.0415
-8.500 -0.6984 0.04332 0.03857 -0.0243 1.0000 0.0335
-8.250 -0.6924 0.04038 0.03526 -0.0221 1.0000 0.0332
-8.000 -0.6861 0.03666 0.03121 -0.0199 1.0000 0.0329
-7.750 -0.6790 0.03322 0.02735 -0.0174 1.0000 0.0329
-7.500 -0.6694 0.02999 0.02370 -0.0149 1.0000 0.0332
-7.250 -0.6573 0.02658 0.01995 -0.0128 1.0000 0.0340
-7.000 -0.6403 0.02488 0.01816 -0.0112 1.0000 0.0354
-6.750 -0.6229 0.02381 0.01700 -0.0095 1.0000 0.0373
-6.500 -0.6062 0.02289 0.01594 -0.0076 1.0000 0.0401
-6.250 -0.5920 0.02213 0.01496 -0.0051 1.0000 0.0420
-6.000 -0.5748 0.02019 0.01296 -0.0037 0.9982 0.0450
-5.750 -0.5293 0.01924 0.01191 -0.0074 0.9879 0.0515
-5.500 -0.4858 0.01788 0.01055 -0.0108 0.9774 0.0597
-5.250 -0.4436 0.01681 0.00944 -0.0138 0.9635 0.0698
-5.000 -0.4032 0.01594 0.00854 -0.0163 0.9463 0.0818
-4.750 -0.3660 0.01522 0.00781 -0.0181 0.9264 0.0949
-4.500 -0.3370 0.01468 0.00723 -0.0180 0.9014 0.1080
-4.250 -0.3128 0.01422 0.00672 -0.0170 0.8764 0.1218
-4.000 -0.2909 0.01377 0.00626 -0.0155 0.8533 0.1374
-3.750 -0.2695 0.01335 0.00585 -0.0140 0.8308 0.1570
-3.500 -0.2482 0.01290 0.00544 -0.0125 0.8105 0.1838
-3.250 -0.2276 0.01238 0.00504 -0.0110 0.7923 0.2272
-3.000 -0.2103 0.01153 0.00466 -0.0092 0.7743 0.3317
-2.750 -0.2030 0.01018 0.00446 -0.0052 0.7582 0.5956
-2.500 -0.1840 0.00991 0.00467 -0.0022 0.7427 0.7485
-2.250 -0.1600 0.01004 0.00480 -0.0003 0.7275 0.8079
-2.000 -0.1340 0.01026 0.00494 0.0012 0.7130 0.8428
-1.750 -0.1077 0.01051 0.00507 0.0025 0.6989 0.8687
-1.500 -0.0779 0.01081 0.00522 0.0032 0.6853 0.8880
-1.250 -0.0452 0.01113 0.00537 0.0031 0.6720 0.9037
-1.000 -0.0084 0.01142 0.00553 0.0022 0.6581 0.9163
-0.750 0.0302 0.01170 0.00566 0.0007 0.6445 0.9280
-0.500 0.0797 0.01209 0.00589 -0.0029 0.6306 0.9409
-0.250 0.1488 0.01258 0.00619 -0.0102 0.6157 0.9559
0.000 0.2073 0.01273 0.00619 -0.0161 0.6015 0.9660
0.250 0.2428 0.01270 0.00605 -0.0178 0.5894 0.9719
0.500 0.2812 0.01263 0.00586 -0.0201 0.5777 0.9768
0.750 0.3139 0.01265 0.00575 -0.0213 0.5673 0.9829
1.000 0.3533 0.01250 0.00554 -0.0240 0.5549 0.9869
1.250 0.3893 0.01243 0.00541 -0.0260 0.5435 0.9918
1.500 0.4259 0.01234 0.00524 -0.0281 0.5329 0.9962
1.750 0.4613 0.01228 0.00508 -0.0300 0.5228 1.0000
2.000 0.4832 0.01229 0.00509 -0.0292 0.5128 1.0000
2.250 0.5052 0.01234 0.00509 -0.0284 0.5040 1.0000
2.500 0.5272 0.01239 0.00510 -0.0275 0.4949 1.0000
2.750 0.5493 0.01246 0.00516 -0.0267 0.4858 1.0000
3.250 0.5935 0.01261 0.00526 -0.0250 0.4682 1.0000
3.500 0.6156 0.01272 0.00534 -0.0242 0.4602 1.0000
3.750 0.6377 0.01281 0.00543 -0.0233 0.4514 1.0000
4.000 0.6598 0.01293 0.00556 -0.0224 0.4429 1.0000
4.250 0.6818 0.01306 0.00566 -0.0214 0.4350 1.0000
4.500 0.7035 0.01320 0.00585 -0.0205 0.4262 1.0000
4.750 0.7254 0.01339 0.00596 -0.0195 0.4189 1.0000
5.000 0.7467 0.01353 0.00619 -0.0184 0.4098 1.0000
5.250 0.7684 0.01374 0.00638 -0.0174 0.4024 1.0000
5.500 0.7896 0.01391 0.00661 -0.0163 0.3937 1.0000
5.750 0.8109 0.01414 0.00685 -0.0152 0.3859 1.0000
6.000 0.8320 0.01434 0.00707 -0.0141 0.3776 1.0000
6.250 0.8529 0.01458 0.00737 -0.0129 0.3692 1.0000
6.500 0.8741 0.01481 0.00758 -0.0118 0.3612 1.0000
6.750 0.8946 0.01505 0.00793 -0.0105 0.3523 1.0000
7.000 0.9158 0.01534 0.00818 -0.0094 0.3445 1.0000
7.250 0.9361 0.01557 0.00853 -0.0081 0.3353 1.0000
7.500 0.9568 0.01586 0.00887 -0.0069 0.3267 1.0000
7.750 0.9775 0.01613 0.00915 -0.0057 0.3179 1.0000
8.000 0.9975 0.01641 0.00954 -0.0045 0.3080 1.0000
8.250 1.0179 0.01672 0.00988 -0.0032 0.2988 1.0000
8.500 1.0376 0.01699 0.01017 -0.0019 0.2881 1.0000
8.750 1.0557 0.01718 0.01042 -0.0004 0.2743 1.0000
9.000 1.0729 0.01738 0.01067 0.0012 0.2579 1.0000
9.250 1.0908 0.01766 0.01103 0.0026 0.2420 1.0000
9.500 1.1086 0.01803 0.01147 0.0040 0.2268 1.0000
9.750 1.1259 0.01847 0.01198 0.0054 0.2109 1.0000
10.000 1.1419 0.01900 0.01254 0.0069 0.1930 1.0000
10.250 1.1558 0.01967 0.01320 0.0086 0.1721 1.0000
10.500 1.1657 0.02060 0.01405 0.0107 0.1428 1.0000
10.750 1.1645 0.02222 0.01540 0.0138 0.0997 1.0000
11.000 1.1491 0.02439 0.01727 0.0186 0.0646 1.0000
11.250 1.1340 0.02669 0.01946 0.0224 0.0504 1.0000
11.500 1.1269 0.02892 0.02175 0.0245 0.0440 1.0000
11.750 1.1146 0.03194 0.02480 0.0258 0.0398 1.0000
12.000 1.1108 0.03459 0.02758 0.0262 0.0368 1.0000
12.250 1.1059 0.03755 0.03063 0.0262 0.0346 1.0000
12.500 1.0981 0.04098 0.03413 0.0259 0.0327 1.0000
12.750 1.0877 0.04479 0.03799 0.0254 0.0314 1.0000
13.000 1.0821 0.04814 0.04143 0.0250 0.0304 1.0000
13.250 1.0803 0.05120 0.04462 0.0246 0.0289 1.0000
13.500 1.0785 0.05422 0.04773 0.0242 0.0281 1.0000
13.750 1.0761 0.05735 0.05093 0.0238 0.0270 1.0000
14.000 1.0756 0.06026 0.05390 0.0234 0.0262 1.0000
14.250 1.0751 0.06316 0.05683 0.0231 0.0253 1.0000
14.500 1.0773 0.06567 0.05935 0.0234 0.0245 1.0000
14.750 1.0815 0.06796 0.06169 0.0243 0.0234 1.0000
15.000 1.0847 0.07075 0.06461 0.0240 0.0231 1.0000
15.250 1.0855 0.07397 0.06797 0.0231 0.0226 1.0000
15.500 1.0826 0.07784 0.07199 0.0215 0.0215 1.0000
15.750 1.0837 0.08112 0.07540 0.0207 0.0214 1.0000
16.000 1.0816 0.08502 0.07945 0.0195 0.0209 1.0000
16.250 1.0786 0.08913 0.08374 0.0180 0.0207 1.0000
16.500 1.0737 0.09369 0.08845 0.0162 0.0204 1.0000
16.750 1.0659 0.09887 0.09381 0.0138 0.0204 1.0000
17.000 1.0562 0.10454 0.09966 0.0110 0.0203 1.0000
17.250 1.0440 0.11086 0.10617 0.0077 0.0203 1.0000
17.500 1.0286 0.11804 0.11354 0.0036 0.0204 1.0000
17.750 1.0092 0.12641 0.12213 -0.0013 0.0206 1.0000
18.000 0.9864 0.13594 0.13184 -0.0071 0.0209 1.0000
18.250 0.9580 0.14740 0.14351 -0.0142 0.0214 1.0000
18.500 0.9216 0.16196 0.15824 -0.0231 0.0222 1.0000
18.750 0.8791 0.18003 0.17638 -0.0330 0.0234 1.0000
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Polar data table (+)
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