E193 (10.22%) (e193-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E193 (10.22%) (e193-il) Reynolds number: 50,000 Max Cl/Cd: 35.91 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e193-il-50000-n5.txt Download as CSV file: xf-e193-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3705 0.08879 0.08219 -0.0439 1.0000 0.0481
-8.000 -0.3741 0.08570 0.07921 -0.0440 1.0000 0.0478
-7.750 -0.3777 0.08261 0.07623 -0.0442 1.0000 0.0475
-7.500 -0.3819 0.07921 0.07293 -0.0451 1.0000 0.0472
-7.250 -0.3870 0.07577 0.06959 -0.0458 1.0000 0.0470
-7.000 -0.3925 0.07253 0.06643 -0.0460 1.0000 0.0466
-6.750 -0.3993 0.06944 0.06339 -0.0457 1.0000 0.0463
-6.500 -0.4071 0.06641 0.06038 -0.0450 1.0000 0.0460
-6.250 -0.4142 0.06343 0.05737 -0.0442 1.0000 0.0458
-6.000 -0.3959 0.05791 0.05159 -0.0496 0.9912 0.0456
-5.750 -0.3687 0.05196 0.04522 -0.0558 0.9794 0.0454
-5.500 -0.3402 0.04670 0.03941 -0.0606 0.9684 0.0450
-5.250 -0.3087 0.04201 0.03411 -0.0646 0.9588 0.0450
-5.000 -0.2793 0.03821 0.02968 -0.0669 0.9480 0.0454
-4.750 -0.2472 0.03493 0.02573 -0.0688 0.9385 0.0463
-4.500 -0.2105 0.03221 0.02228 -0.0708 0.9308 0.0483
-4.250 -0.1803 0.03047 0.02044 -0.0721 0.9209 0.0527
-4.000 -0.1428 0.02867 0.01821 -0.0739 0.9141 0.0579
-3.750 -0.1108 0.02707 0.01637 -0.0744 0.9049 0.0629
-3.500 -0.0769 0.02583 0.01496 -0.0755 0.8970 0.0753
-3.250 -0.0429 0.02464 0.01374 -0.0768 0.8888 0.1021
-3.000 -0.0123 0.02355 0.01287 -0.0777 0.8798 0.1621
-2.750 0.0206 0.02241 0.01207 -0.0790 0.8724 0.2526
-2.500 0.0463 0.02161 0.01170 -0.0789 0.8627 0.3633
-2.250 0.0746 0.02072 0.01135 -0.0785 0.8560 0.5163
-2.000 0.0932 0.02008 0.01131 -0.0756 0.8461 0.6855
-1.750 0.1790 0.01932 0.01055 -0.0850 0.8440 1.0000
-1.500 0.2039 0.01947 0.01032 -0.0848 0.8339 1.0000
-1.250 0.2346 0.01954 0.01003 -0.0854 0.8264 1.0000
-1.000 0.2568 0.01979 0.01000 -0.0846 0.8160 1.0000
-0.750 0.2832 0.01998 0.00991 -0.0845 0.8076 1.0000
-0.500 0.3096 0.02018 0.00987 -0.0843 0.7993 1.0000
-0.250 0.3340 0.02046 0.00995 -0.0839 0.7906 1.0000
0.000 0.3620 0.02065 0.00993 -0.0839 0.7833 1.0000
0.250 0.3849 0.02100 0.01013 -0.0832 0.7745 1.0000
0.500 0.4134 0.02119 0.01017 -0.0833 0.7679 1.0000
0.750 0.4353 0.02160 0.01047 -0.0825 0.7590 1.0000
1.000 0.4639 0.02181 0.01056 -0.0825 0.7527 1.0000
1.250 0.4852 0.02227 0.01095 -0.0817 0.7438 1.0000
1.500 0.5136 0.02250 0.01109 -0.0817 0.7379 1.0000
1.750 0.5343 0.02302 0.01158 -0.0808 0.7290 1.0000
2.000 0.5626 0.02326 0.01176 -0.0808 0.7231 1.0000
2.250 0.5829 0.02383 0.01233 -0.0799 0.7144 1.0000
2.500 0.6109 0.02408 0.01258 -0.0797 0.7084 1.0000
2.750 0.6308 0.02470 0.01322 -0.0788 0.6997 1.0000
3.000 0.6586 0.02497 0.01350 -0.0787 0.6937 1.0000
3.250 0.6781 0.02564 0.01421 -0.0777 0.6849 1.0000
3.500 0.7059 0.02591 0.01454 -0.0775 0.6788 1.0000
3.750 0.7246 0.02662 0.01533 -0.0764 0.6697 1.0000
4.000 0.7532 0.02684 0.01561 -0.0762 0.6635 1.0000
4.250 0.7709 0.02761 0.01647 -0.0750 0.6537 1.0000
4.500 0.8015 0.02770 0.01667 -0.0750 0.6478 1.0000
4.750 0.8179 0.02850 0.01760 -0.0736 0.6370 1.0000
5.000 0.8399 0.02900 0.01823 -0.0727 0.6279 1.0000
5.250 0.8673 0.02915 0.01854 -0.0721 0.6196 1.0000
5.500 0.8855 0.02979 0.01933 -0.0708 0.6082 1.0000
5.750 0.9078 0.03015 0.01985 -0.0696 0.5975 1.0000
6.000 0.9375 0.03001 0.01986 -0.0690 0.5880 1.0000
6.250 0.9588 0.03028 0.02035 -0.0677 0.5753 1.0000
6.500 0.9796 0.03051 0.02077 -0.0662 0.5616 1.0000
6.750 1.0016 0.03056 0.02103 -0.0646 0.5471 1.0000
7.000 1.0248 0.03045 0.02111 -0.0631 0.5316 1.0000
7.250 1.0453 0.03040 0.02130 -0.0612 0.5143 1.0000
7.500 1.0603 0.03064 0.02176 -0.0589 0.4941 1.0000
7.750 1.0818 0.03032 0.02161 -0.0568 0.4726 1.0000
8.000 1.0933 0.03064 0.02214 -0.0541 0.4472 1.0000
8.250 1.1063 0.03081 0.02244 -0.0513 0.4175 1.0000
8.500 1.1162 0.03118 0.02291 -0.0484 0.3822 1.0000
8.750 1.1227 0.03179 0.02344 -0.0451 0.3411 1.0000
9.000 1.1234 0.03287 0.02432 -0.0414 0.2975 1.0000
9.250 1.1201 0.03455 0.02571 -0.0381 0.2572 1.0000
9.500 1.1147 0.03672 0.02768 -0.0353 0.2214 1.0000
9.750 1.1083 0.03926 0.03001 -0.0330 0.1906 1.0000
10.000 1.1005 0.04216 0.03270 -0.0313 0.1617 1.0000
10.250 1.0935 0.04523 0.03560 -0.0301 0.1355 1.0000
10.500 1.0865 0.04852 0.03871 -0.0293 0.1107 1.0000
10.750 1.0807 0.05186 0.04188 -0.0287 0.0931 1.0000
11.000 1.0772 0.05514 0.04513 -0.0280 0.0780 1.0000
11.250 1.0743 0.05843 0.04836 -0.0275 0.0682 1.0000
11.500 1.0750 0.06143 0.05148 -0.0268 0.0601 1.0000
11.750 1.0762 0.06444 0.05457 -0.0262 0.0535 1.0000
12.000 1.0785 0.06735 0.05754 -0.0258 0.0490 1.0000
12.250 1.0839 0.07003 0.06032 -0.0250 0.0455 1.0000
12.500 1.0940 0.07245 0.06301 -0.0239 0.0425 1.0000
12.750 1.1033 0.07501 0.06577 -0.0230 0.0403 1.0000
13.000 1.1120 0.07769 0.06857 -0.0223 0.0386 1.0000
13.250 1.1205 0.08067 0.07168 -0.0217 0.0372 1.0000
13.500 1.1190 0.08495 0.07634 -0.0221 0.0363 1.0000
13.750 1.1132 0.08978 0.08150 -0.0231 0.0356 1.0000
14.000 1.1030 0.09528 0.08731 -0.0249 0.0351 1.0000
14.250 1.0912 0.10122 0.09356 -0.0272 0.0349 1.0000
14.500 1.0759 0.10801 0.10056 -0.0304 0.0348 1.0000
14.750 1.0590 0.11558 0.10835 -0.0344 0.0350 1.0000
15.000 1.0413 0.12391 0.11687 -0.0391 0.0353 1.0000
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Polar data table (+)
Polar graphs
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