E193 (10.22%) (e193-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E193 (10.22%) (e193-il) Reynolds number: 100,000 Max Cl/Cd: 58.85 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e193-il-100000-n5.txt Download as CSV file: xf-e193-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3820 0.07812 0.07357 -0.0450 1.0000 0.0290
-7.750 -0.3864 0.07570 0.07124 -0.0442 1.0000 0.0287
-7.500 -0.3926 0.07269 0.06833 -0.0444 1.0000 0.0283
-7.250 -0.4017 0.06971 0.06543 -0.0443 1.0000 0.0280
-7.000 -0.3819 0.06284 0.05847 -0.0533 0.9880 0.0272
-6.750 -0.3599 0.05485 0.05026 -0.0627 0.9742 0.0262
-6.500 -0.3395 0.04651 0.04150 -0.0703 0.9600 0.0252
-6.250 -0.3181 0.03953 0.03389 -0.0750 0.9465 0.0245
-6.000 -0.2945 0.03430 0.02795 -0.0774 0.9336 0.0241
-5.750 -0.2679 0.03063 0.02368 -0.0789 0.9218 0.0242
-5.500 -0.2387 0.02783 0.02033 -0.0800 0.9113 0.0245
-5.250 -0.2080 0.02565 0.01772 -0.0810 0.9014 0.0253
-5.000 -0.1789 0.02404 0.01576 -0.0815 0.8897 0.0272
-4.750 -0.1488 0.02256 0.01385 -0.0817 0.8788 0.0290
-4.500 -0.1195 0.02102 0.01216 -0.0821 0.8688 0.0302
-4.250 -0.0914 0.01992 0.01092 -0.0821 0.8578 0.0319
-4.000 -0.0642 0.01900 0.00985 -0.0819 0.8464 0.0341
-3.750 -0.0367 0.01819 0.00885 -0.0816 0.8360 0.0376
-3.500 -0.0091 0.01744 0.00799 -0.0815 0.8265 0.0464
-3.250 0.0165 0.01664 0.00721 -0.0810 0.8155 0.0650
-3.000 0.0426 0.01594 0.00667 -0.0808 0.8060 0.1156
-2.750 0.0685 0.01527 0.00639 -0.0807 0.7972 0.2063
-2.500 0.0938 0.01483 0.00612 -0.0803 0.7874 0.2799
-2.250 0.1198 0.01440 0.00590 -0.0799 0.7793 0.3676
-2.000 0.1448 0.01398 0.00576 -0.0793 0.7704 0.4722
-1.750 0.1683 0.01355 0.00567 -0.0782 0.7624 0.5916
-1.500 0.1913 0.01313 0.00561 -0.0763 0.7547 0.7292
-1.250 0.2395 0.01280 0.00546 -0.0792 0.7478 0.9053
-1.000 0.2974 0.01272 0.00514 -0.0852 0.7405 0.9965
-0.750 0.3239 0.01282 0.00504 -0.0851 0.7331 1.0000
-0.500 0.3483 0.01293 0.00497 -0.0845 0.7255 1.0000
-0.250 0.3729 0.01306 0.00493 -0.0839 0.7185 1.0000
0.000 0.3976 0.01320 0.00493 -0.0833 0.7112 1.0000
0.250 0.4228 0.01334 0.00493 -0.0828 0.7047 1.0000
0.500 0.4475 0.01350 0.00499 -0.0822 0.6975 1.0000
0.750 0.4734 0.01364 0.00500 -0.0818 0.6918 1.0000
1.000 0.4980 0.01383 0.00514 -0.0812 0.6843 1.0000
1.250 0.5240 0.01399 0.00519 -0.0808 0.6786 1.0000
1.500 0.5488 0.01419 0.00536 -0.0803 0.6717 1.0000
1.750 0.5745 0.01436 0.00548 -0.0799 0.6655 1.0000
2.000 0.6000 0.01456 0.00564 -0.0795 0.6594 1.0000
2.250 0.6252 0.01477 0.00585 -0.0791 0.6527 1.0000
2.500 0.6517 0.01495 0.00598 -0.0787 0.6475 1.0000
2.750 0.6762 0.01520 0.00627 -0.0782 0.6402 1.0000
3.000 0.7024 0.01539 0.00644 -0.0778 0.6344 1.0000
3.250 0.7272 0.01564 0.00675 -0.0774 0.6275 1.0000
3.500 0.7529 0.01584 0.00698 -0.0769 0.6210 1.0000
3.750 0.7780 0.01608 0.00725 -0.0765 0.6140 1.0000
4.000 0.8032 0.01628 0.00753 -0.0760 0.6065 1.0000
4.250 0.8281 0.01651 0.00781 -0.0754 0.5986 1.0000
4.500 0.8535 0.01668 0.00803 -0.0749 0.5905 1.0000
4.750 0.8774 0.01690 0.00835 -0.0741 0.5809 1.0000
5.000 0.9027 0.01705 0.00857 -0.0735 0.5718 1.0000
5.250 0.9269 0.01721 0.00882 -0.0727 0.5611 1.0000
5.500 0.9503 0.01739 0.00911 -0.0719 0.5492 1.0000
5.750 0.9738 0.01754 0.00937 -0.0710 0.5367 1.0000
6.000 0.9971 0.01770 0.00966 -0.0700 0.5232 1.0000
6.250 1.0199 0.01785 0.00992 -0.0690 0.5082 1.0000
6.500 1.0422 0.01802 0.01020 -0.0679 0.4913 1.0000
6.750 1.0641 0.01819 0.01045 -0.0666 0.4726 1.0000
7.000 1.0843 0.01845 0.01085 -0.0652 0.4492 1.0000
7.250 1.1034 0.01875 0.01120 -0.0636 0.4207 1.0000
7.500 1.1205 0.01917 0.01159 -0.0618 0.3841 1.0000
7.750 1.1325 0.01990 0.01208 -0.0592 0.3289 1.0000
8.000 1.1383 0.02111 0.01289 -0.0561 0.2640 1.0000
8.250 1.1404 0.02265 0.01405 -0.0528 0.2043 1.0000
8.500 1.1421 0.02426 0.01530 -0.0496 0.1535 1.0000
8.750 1.1436 0.02576 0.01654 -0.0465 0.1155 1.0000
9.000 1.1459 0.02721 0.01783 -0.0435 0.0873 1.0000
9.250 1.1486 0.02872 0.01926 -0.0407 0.0660 1.0000
9.500 1.1495 0.03047 0.02092 -0.0380 0.0488 1.0000
9.750 1.1506 0.03233 0.02277 -0.0356 0.0392 1.0000
10.000 1.1517 0.03431 0.02481 -0.0335 0.0330 1.0000
10.250 1.1531 0.03634 0.02689 -0.0318 0.0296 1.0000
10.500 1.1550 0.03845 0.02914 -0.0302 0.0268 1.0000
10.750 1.1581 0.04052 0.03134 -0.0290 0.0248 1.0000
11.000 1.1601 0.04278 0.03371 -0.0279 0.0233 1.0000
11.250 1.1606 0.04527 0.03631 -0.0269 0.0225 1.0000
11.500 1.1611 0.04786 0.03899 -0.0260 0.0218 1.0000
11.750 1.1643 0.05027 0.04158 -0.0252 0.0211 1.0000
12.000 1.1681 0.05269 0.04416 -0.0244 0.0205 1.0000
12.250 1.1725 0.05514 0.04676 -0.0236 0.0200 1.0000
12.500 1.1775 0.05763 0.04940 -0.0229 0.0194 1.0000
12.750 1.1826 0.06017 0.05212 -0.0223 0.0190 1.0000
13.000 1.1874 0.06285 0.05496 -0.0217 0.0185 1.0000
13.250 1.1907 0.06571 0.05797 -0.0215 0.0181 1.0000
13.500 1.1927 0.06874 0.06114 -0.0214 0.0177 1.0000
13.750 1.1929 0.07198 0.06449 -0.0215 0.0172 1.0000
14.000 1.1918 0.07563 0.06829 -0.0218 0.0168 1.0000
14.250 1.1891 0.07957 0.07248 -0.0223 0.0167 1.0000
14.500 1.1808 0.08431 0.07753 -0.0236 0.0163 1.0000
14.750 1.1727 0.08927 0.08274 -0.0250 0.0162 1.0000
15.000 1.1619 0.09477 0.08851 -0.0271 0.0161 1.0000
15.250 1.1493 0.10084 0.09482 -0.0297 0.0160 1.0000
15.500 1.1361 0.10730 0.10150 -0.0329 0.0160 1.0000
15.750 1.1207 0.11454 0.10897 -0.0368 0.0160 1.0000
16.000 1.1040 0.12249 0.11713 -0.0414 0.0161 1.0000
16.250 1.0867 0.13110 0.12593 -0.0467 0.0162 1.0000
16.500 1.0682 0.14072 0.13571 -0.0528 0.0163 1.0000
16.750 1.0505 0.15085 0.14597 -0.0592 0.0165 1.0000
17.000 1.0359 0.16070 0.15589 -0.0653 0.0168 1.0000
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Polar data table (+)
Polar graphs
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