EH 2.0/12 (eh2012-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 2.0/12 (eh2012-il) Reynolds number: 100,000 Max Cl/Cd: 42.5 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh2012-il-100000.txt Download as CSV file: xf-eh2012-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4939 0.09520 0.09061 -0.0086 1.0000 0.1280
-9.000 -0.5161 0.09038 0.08589 -0.0146 1.0000 0.1327
-8.750 -0.5552 0.08523 0.08081 -0.0212 1.0000 0.1336
-8.500 -0.5183 0.08139 0.07702 -0.0172 1.0000 0.1388
-8.250 -0.5247 0.07743 0.07310 -0.0188 1.0000 0.1423
-8.000 -0.5645 0.07376 0.06936 -0.0215 1.0000 0.1477
-7.750 -0.6207 0.05498 0.04959 -0.0245 1.0000 0.0791
-7.500 -0.6089 0.05087 0.04539 -0.0234 1.0000 0.0753
-7.250 -0.6064 0.04610 0.04035 -0.0215 1.0000 0.0719
-7.000 -0.6149 0.03940 0.03263 -0.0173 1.0000 0.0665
-6.750 -0.6045 0.03614 0.02902 -0.0149 1.0000 0.0668
-6.500 -0.5883 0.03451 0.02741 -0.0135 1.0000 0.0702
-6.250 -0.5765 0.03244 0.02504 -0.0110 1.0000 0.0735
-6.000 -0.5656 0.03024 0.02238 -0.0080 1.0000 0.0763
-5.750 -0.5553 0.02811 0.01986 -0.0050 1.0000 0.0789
-5.500 -0.5455 0.02697 0.01884 -0.0027 1.0000 0.0840
-5.250 -0.5380 0.02607 0.01770 0.0004 1.0000 0.0894
-5.000 -0.5231 0.02460 0.01612 0.0018 0.9985 0.0950
-4.750 -0.4718 0.02302 0.01442 -0.0030 0.9863 0.1107
-4.500 -0.4210 0.02168 0.01301 -0.0077 0.9736 0.1299
-4.250 -0.3706 0.02030 0.01167 -0.0122 0.9609 0.1523
-4.000 -0.3203 0.01906 0.01053 -0.0166 0.9482 0.1809
-3.750 -0.2758 0.01784 0.00957 -0.0198 0.9334 0.2180
-3.500 -0.2391 0.01656 0.00872 -0.0214 0.9167 0.2780
-3.250 -0.2218 0.01444 0.00818 -0.0193 0.8989 0.5263
-3.000 -0.1876 0.01469 0.00927 -0.0158 0.8839 0.8103
-2.750 -0.1481 0.01552 0.00988 -0.0146 0.8673 0.8648
-2.500 -0.0899 0.01639 0.01043 -0.0172 0.8504 0.8974
-2.250 -0.0190 0.01697 0.01069 -0.0231 0.8315 0.9226
-2.000 0.0425 0.01720 0.01061 -0.0282 0.8117 0.9449
-1.750 0.1020 0.01713 0.01024 -0.0336 0.7923 0.9661
-1.500 0.1872 0.01646 0.00929 -0.0444 0.7699 0.9959
-1.250 0.2162 0.01624 0.00888 -0.0452 0.7517 1.0000
-1.000 0.2350 0.01620 0.00868 -0.0440 0.7354 1.0000
-0.750 0.2542 0.01619 0.00852 -0.0428 0.7200 1.0000
-0.500 0.2738 0.01619 0.00840 -0.0417 0.7053 1.0000
-0.250 0.2938 0.01621 0.00830 -0.0406 0.6911 1.0000
0.000 0.3141 0.01625 0.00823 -0.0396 0.6776 1.0000
0.250 0.3345 0.01631 0.00819 -0.0386 0.6648 1.0000
0.500 0.3551 0.01637 0.00816 -0.0375 0.6525 1.0000
0.750 0.3759 0.01645 0.00811 -0.0364 0.6414 1.0000
1.000 0.3970 0.01655 0.00816 -0.0355 0.6291 1.0000
1.250 0.4182 0.01667 0.00824 -0.0346 0.6171 1.0000
1.500 0.4395 0.01681 0.00833 -0.0337 0.6061 1.0000
1.750 0.4610 0.01692 0.00833 -0.0326 0.5964 1.0000
2.000 0.4824 0.01708 0.00848 -0.0317 0.5848 1.0000
2.250 0.5038 0.01727 0.00867 -0.0307 0.5740 1.0000
2.500 0.5253 0.01745 0.00879 -0.0297 0.5646 1.0000
2.750 0.5466 0.01765 0.00896 -0.0286 0.5544 1.0000
3.000 0.5676 0.01792 0.00926 -0.0277 0.5440 1.0000
3.250 0.5891 0.01814 0.00941 -0.0266 0.5352 1.0000
3.500 0.6102 0.01839 0.00970 -0.0255 0.5252 1.0000
3.750 0.6309 0.01872 0.01006 -0.0244 0.5153 1.0000
4.000 0.6531 0.01892 0.01016 -0.0233 0.5075 1.0000
4.250 0.6730 0.01930 0.01065 -0.0221 0.4969 1.0000
4.500 0.6937 0.01965 0.01104 -0.0210 0.4879 1.0000
4.750 0.7154 0.01990 0.01126 -0.0198 0.4794 1.0000
5.000 0.7350 0.02036 0.01182 -0.0186 0.4695 1.0000
5.250 0.7570 0.02064 0.01206 -0.0175 0.4617 1.0000
5.500 0.7768 0.02106 0.01259 -0.0162 0.4519 1.0000
5.750 0.7969 0.02151 0.01312 -0.0149 0.4429 1.0000
6.000 0.8193 0.02178 0.01335 -0.0138 0.4347 1.0000
6.250 0.8378 0.02235 0.01408 -0.0125 0.4248 1.0000
6.500 0.8600 0.02269 0.01442 -0.0114 0.4167 1.0000
6.750 0.8801 0.02312 0.01495 -0.0101 0.4070 1.0000
7.000 0.8994 0.02367 0.01562 -0.0088 0.3976 1.0000
7.250 0.9242 0.02385 0.01571 -0.0079 0.3895 1.0000
7.500 0.9413 0.02448 0.01658 -0.0064 0.3789 1.0000
7.750 0.9612 0.02497 0.01717 -0.0051 0.3693 1.0000
8.000 0.9859 0.02516 0.01730 -0.0043 0.3605 1.0000
8.250 1.0028 0.02576 0.01811 -0.0027 0.3495 1.0000
8.500 1.0221 0.02628 0.01874 -0.0014 0.3392 1.0000
8.750 1.0454 0.02649 0.01897 -0.0004 0.3291 1.0000
9.000 1.0663 0.02676 0.01931 0.0008 0.3178 1.0000
9.250 1.0837 0.02722 0.01993 0.0024 0.3056 1.0000
9.500 1.1024 0.02730 0.02009 0.0039 0.2918 1.0000
9.750 1.1212 0.02686 0.01958 0.0055 0.2749 1.0000
10.000 1.1341 0.02672 0.01954 0.0077 0.2569 1.0000
10.250 1.1449 0.02694 0.01991 0.0099 0.2398 1.0000
10.500 1.1543 0.02730 0.02039 0.0122 0.2226 1.0000
10.750 1.1601 0.02779 0.02093 0.0148 0.2038 1.0000
11.000 1.1596 0.02870 0.02196 0.0178 0.1813 1.0000
11.250 1.1492 0.03006 0.02328 0.0217 0.1576 1.0000
11.500 1.1325 0.03229 0.02538 0.0249 0.1351 1.0000
11.750 1.1129 0.03554 0.02852 0.0266 0.1128 1.0000
12.000 1.0943 0.03936 0.03221 0.0272 0.0982 1.0000
12.250 1.0781 0.04342 0.03618 0.0272 0.0864 1.0000
12.500 1.0664 0.04727 0.03998 0.0270 0.0776 1.0000
12.750 1.0576 0.05079 0.04335 0.0271 0.0711 1.0000
13.000 1.0545 0.05400 0.04668 0.0269 0.0651 1.0000
13.250 1.0534 0.05675 0.04926 0.0274 0.0596 1.0000
13.500 1.0550 0.05958 0.05230 0.0275 0.0560 1.0000
13.750 1.0599 0.06196 0.05469 0.0280 0.0523 1.0000
14.000 1.0800 0.06305 0.05565 0.0306 0.0489 1.0000
14.250 1.0795 0.06643 0.05928 0.0301 0.0474 1.0000
14.500 1.0777 0.07001 0.06307 0.0295 0.0458 1.0000
14.750 1.0738 0.07386 0.06710 0.0285 0.0444 1.0000
15.000 1.0698 0.07787 0.07127 0.0273 0.0433 1.0000
15.250 1.0647 0.08207 0.07563 0.0259 0.0424 1.0000
15.500 1.0597 0.08641 0.08009 0.0244 0.0414 1.0000
15.750 1.0465 0.09216 0.08608 0.0217 0.0416 1.0000
16.000 1.0305 0.09859 0.09271 0.0185 0.0414 1.0000
16.250 1.0018 0.10766 0.10208 0.0129 0.0422 1.0000
16.500 0.9446 0.12374 0.11852 0.0024 0.0452 1.0000
16.750 0.9016 0.13854 0.13344 -0.0064 0.0480 1.0000
17.000 0.8745 0.15058 0.14547 -0.0129 0.0491 1.0000
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Polar data table (+)
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