E193 (10.22%) (e193-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: E193 (10.22%) (e193-il) Reynolds number: 100,000 Max Cl/Cd: 58.66 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e193-il-100000.txt Download as CSV file: xf-e193-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E193 (10.22%)
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3411 0.09300 0.08834 -0.0363 1.0000 0.1010
-8.000 -0.3586 0.09119 0.08670 -0.0385 1.0000 0.1034
-7.750 -0.3809 0.08950 0.08519 -0.0404 1.0000 0.1040
-7.500 -0.3658 0.08525 0.08095 -0.0364 1.0000 0.1073
-7.250 -0.3627 0.08303 0.07880 -0.0341 1.0000 0.1112
-7.000 -0.3768 0.08122 0.07713 -0.0331 1.0000 0.1146
-6.750 -0.3646 0.07076 0.06722 -0.0362 0.9894 0.1197
-6.500 -0.3307 0.06677 0.06323 -0.0323 0.9866 0.1254
-6.250 -0.4367 0.07536 0.07148 -0.0359 0.9969 0.1198
-6.000 -0.4087 0.07231 0.06850 -0.0337 0.9920 0.1247
-5.750 -0.3765 0.06602 0.06205 -0.0454 0.9815 0.1362
-5.500 -0.3422 0.06076 0.05660 -0.0544 0.9725 0.1498
-5.250 -0.3123 0.05656 0.05222 -0.0602 0.9619 0.1640
-5.000 -0.2814 0.05307 0.04870 -0.0624 0.9542 0.1727
-4.750 -0.2325 0.03475 0.02783 -0.0743 0.9457 0.0639
-4.500 -0.2010 0.03125 0.02401 -0.0758 0.9371 0.0617
-4.250 -0.1601 0.02814 0.02030 -0.0785 0.9313 0.0614
-4.000 -0.1257 0.02622 0.01783 -0.0796 0.9228 0.0641
-3.750 -0.0838 0.02381 0.01525 -0.0822 0.9175 0.0675
-3.500 -0.0476 0.02233 0.01359 -0.0835 0.9101 0.0729
-3.250 -0.0098 0.02085 0.01209 -0.0850 0.9035 0.0859
-3.000 0.0217 0.01937 0.01082 -0.0855 0.8957 0.1287
-2.750 0.0535 0.01806 0.01013 -0.0865 0.8884 0.2529
-2.500 0.0787 0.01703 0.00981 -0.0861 0.8797 0.4060
-2.250 0.1060 0.01601 0.00960 -0.0853 0.8730 0.6151
-2.000 0.1815 0.01497 0.00917 -0.0915 0.8719 0.9539
-1.750 0.2423 0.01483 0.00864 -0.0983 0.8648 1.0000
-1.500 0.2716 0.01482 0.00834 -0.0986 0.8569 1.0000
-1.250 0.2919 0.01506 0.00836 -0.0975 0.8461 1.0000
-1.000 0.3171 0.01521 0.00830 -0.0970 0.8377 1.0000
-0.750 0.3416 0.01537 0.00829 -0.0963 0.8291 1.0000
-0.500 0.3636 0.01565 0.00842 -0.0954 0.8201 1.0000
-0.250 0.3905 0.01578 0.00838 -0.0950 0.8130 1.0000
0.000 0.4114 0.01614 0.00864 -0.0939 0.8037 1.0000
0.250 0.4392 0.01626 0.00861 -0.0936 0.7975 1.0000
0.500 0.4594 0.01670 0.00898 -0.0925 0.7882 1.0000
0.750 0.4876 0.01682 0.00898 -0.0923 0.7823 1.0000
1.000 0.5076 0.01730 0.00943 -0.0912 0.7730 1.0000
1.250 0.5360 0.01744 0.00947 -0.0910 0.7675 1.0000
1.500 0.5559 0.01798 0.01000 -0.0899 0.7582 1.0000
1.750 0.5843 0.01812 0.01007 -0.0897 0.7528 1.0000
2.000 0.6041 0.01871 0.01067 -0.0887 0.7437 1.0000
2.250 0.6326 0.01885 0.01076 -0.0884 0.7382 1.0000
2.500 0.6522 0.01948 0.01144 -0.0875 0.7291 1.0000
2.750 0.6810 0.01961 0.01153 -0.0872 0.7235 1.0000
3.000 0.7004 0.02027 0.01224 -0.0862 0.7142 1.0000
3.250 0.7297 0.02036 0.01231 -0.0860 0.7086 1.0000
3.500 0.7489 0.02101 0.01306 -0.0849 0.6989 1.0000
3.750 0.7794 0.02101 0.01305 -0.0847 0.6933 1.0000
4.000 0.7984 0.02165 0.01378 -0.0835 0.6828 1.0000
4.250 0.8233 0.02194 0.01413 -0.0828 0.6747 1.0000
4.500 0.8497 0.02208 0.01433 -0.0821 0.6661 1.0000
4.750 0.8715 0.02248 0.01484 -0.0811 0.6558 1.0000
5.000 0.9022 0.02230 0.01467 -0.0806 0.6481 1.0000
5.250 0.9251 0.02251 0.01502 -0.0795 0.6368 1.0000
5.500 0.9485 0.02267 0.01528 -0.0784 0.6251 1.0000
5.750 0.9744 0.02260 0.01530 -0.0774 0.6136 1.0000
6.000 1.0026 0.02234 0.01510 -0.0765 0.6021 1.0000
6.250 1.0313 0.02197 0.01481 -0.0757 0.5897 1.0000
6.500 1.0571 0.02171 0.01466 -0.0745 0.5753 1.0000
6.750 1.0798 0.02155 0.01464 -0.0730 0.5588 1.0000
7.000 1.1024 0.02130 0.01455 -0.0713 0.5403 1.0000
7.250 1.1267 0.02084 0.01419 -0.0697 0.5201 1.0000
7.500 1.1473 0.02054 0.01402 -0.0677 0.4959 1.0000
7.750 1.1657 0.02022 0.01378 -0.0653 0.4642 1.0000
8.000 1.1790 0.02010 0.01361 -0.0622 0.4173 1.0000
8.250 1.1845 0.02064 0.01387 -0.0583 0.3469 1.0000
8.500 1.1833 0.02201 0.01472 -0.0540 0.2701 1.0000
8.750 1.1793 0.02381 0.01607 -0.0498 0.2090 1.0000
9.000 1.1711 0.02580 0.01767 -0.0453 0.1588 1.0000
9.250 1.1589 0.02813 0.01963 -0.0405 0.1178 1.0000
9.500 1.1461 0.03086 0.02206 -0.0363 0.0875 1.0000
9.750 1.1380 0.03354 0.02455 -0.0330 0.0717 1.0000
10.000 1.1396 0.03576 0.02676 -0.0306 0.0619 1.0000
10.250 1.1464 0.03789 0.02886 -0.0286 0.0558 1.0000
10.500 1.1564 0.03977 0.03073 -0.0271 0.0503 1.0000
10.750 1.1836 0.04200 0.03294 -0.0260 0.0468 1.0000
11.000 1.2127 0.04423 0.03539 -0.0254 0.0446 1.0000
11.250 1.2412 0.04705 0.03847 -0.0250 0.0429 1.0000
11.500 1.2613 0.05014 0.04185 -0.0243 0.0420 1.0000
11.750 1.2723 0.05326 0.04526 -0.0230 0.0414 1.0000
12.000 1.2774 0.05606 0.04825 -0.0216 0.0401 1.0000
12.250 1.2804 0.05937 0.05179 -0.0203 0.0392 1.0000
12.500 1.2793 0.06327 0.05593 -0.0190 0.0387 1.0000
12.750 1.2706 0.06691 0.05986 -0.0175 0.0387 1.0000
13.000 1.2574 0.07060 0.06387 -0.0162 0.0389 1.0000
13.250 1.2394 0.07468 0.06828 -0.0155 0.0393 1.0000
13.500 1.2153 0.07964 0.07359 -0.0157 0.0399 1.0000
13.750 1.1824 0.08586 0.08017 -0.0173 0.0406 1.0000
14.000 1.1505 0.09297 0.08756 -0.0201 0.0413 1.0000
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Polar data table (+)
Polar graphs
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