E224 (10.17%) (e224-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E224 (10.17%) (e224-il) Reynolds number: 100,000 Max Cl/Cd: 50.22 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e224-il-100000-n5.txt Download as CSV file: xf-e224-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E224 (10.17%)
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5448 0.07637 0.07133 -0.0399 1.0000 0.0189
-9.750 -0.5553 0.07002 0.06500 -0.0442 1.0000 0.0186
-9.500 -0.5741 0.06286 0.05780 -0.0502 1.0000 0.0184
-9.250 -0.5895 0.05847 0.05338 -0.0527 1.0000 0.0180
-9.000 -0.6098 0.05464 0.04943 -0.0529 1.0000 0.0179
-8.750 -0.6251 0.05058 0.04515 -0.0524 1.0000 0.0180
-8.500 -0.6344 0.04677 0.04102 -0.0512 1.0000 0.0182
-8.250 -0.6378 0.04323 0.03709 -0.0497 1.0000 0.0185
-7.750 -0.6307 0.03706 0.03024 -0.0464 1.0000 0.0196
-7.500 -0.6207 0.03471 0.02763 -0.0448 1.0000 0.0201
-7.250 -0.6087 0.03235 0.02497 -0.0432 1.0000 0.0206
-7.000 -0.5947 0.03022 0.02255 -0.0416 1.0000 0.0212
-6.750 -0.5789 0.02830 0.02032 -0.0400 1.0000 0.0219
-6.500 -0.5621 0.02654 0.01830 -0.0384 1.0000 0.0230
-6.250 -0.5444 0.02497 0.01651 -0.0368 1.0000 0.0242
-6.000 -0.5262 0.02362 0.01497 -0.0353 1.0000 0.0262
-5.750 -0.5088 0.02245 0.01378 -0.0341 1.0000 0.0296
-5.500 -0.4900 0.02142 0.01262 -0.0327 1.0000 0.0335
-5.250 -0.4714 0.02023 0.01133 -0.0314 1.0000 0.0381
-5.000 -0.4515 0.01947 0.01045 -0.0303 1.0000 0.0474
-4.750 -0.4305 0.01852 0.00955 -0.0296 0.9996 0.0622
-4.500 -0.3958 0.01754 0.00868 -0.0316 0.9945 0.0935
-4.250 -0.3621 0.01671 0.00807 -0.0335 0.9887 0.1447
-4.000 -0.3267 0.01608 0.00766 -0.0357 0.9833 0.2104
-3.750 -0.2942 0.01554 0.00731 -0.0372 0.9763 0.2752
-3.500 -0.2583 0.01514 0.00706 -0.0392 0.9705 0.3384
-3.250 -0.2265 0.01478 0.00684 -0.0402 0.9627 0.3959
-3.000 -0.1907 0.01448 0.00668 -0.0419 0.9568 0.4542
-2.750 -0.1597 0.01422 0.00651 -0.0425 0.9485 0.5063
-2.500 -0.1234 0.01400 0.00639 -0.0441 0.9427 0.5585
-2.250 -0.0927 0.01381 0.00629 -0.0445 0.9340 0.6048
-2.000 -0.0563 0.01363 0.00617 -0.0458 0.9283 0.6512
-1.750 -0.0272 0.01350 0.00609 -0.0457 0.9187 0.6918
-1.500 0.0056 0.01336 0.00600 -0.0461 0.9112 0.7319
-1.250 0.0360 0.01325 0.00593 -0.0460 0.9020 0.7698
-1.000 0.0651 0.01315 0.00585 -0.0456 0.8921 0.8048
-0.750 0.0978 0.01304 0.00574 -0.0459 0.8839 0.8387
-0.500 0.1285 0.01296 0.00566 -0.0458 0.8733 0.8709
-0.250 0.1627 0.01288 0.00556 -0.0466 0.8627 0.9012
0.000 0.2029 0.01278 0.00543 -0.0486 0.8528 0.9288
0.250 0.2482 0.01266 0.00526 -0.0517 0.8427 0.9518
0.500 0.2929 0.01257 0.00512 -0.0550 0.8299 0.9732
0.750 0.3384 0.01246 0.00497 -0.0585 0.8162 0.9924
1.000 0.3702 0.01242 0.00487 -0.0593 0.8010 1.0000
1.250 0.3943 0.01242 0.00481 -0.0585 0.7847 1.0000
1.500 0.4176 0.01246 0.00480 -0.0576 0.7673 1.0000
1.750 0.4418 0.01252 0.00479 -0.0567 0.7497 1.0000
2.000 0.4666 0.01259 0.00482 -0.0559 0.7319 1.0000
2.250 0.4917 0.01267 0.00484 -0.0552 0.7138 1.0000
2.500 0.5159 0.01279 0.00492 -0.0543 0.6939 1.0000
2.750 0.5407 0.01291 0.00502 -0.0535 0.6741 1.0000
3.000 0.5654 0.01306 0.00512 -0.0527 0.6532 1.0000
3.250 0.5900 0.01323 0.00525 -0.0519 0.6316 1.0000
3.500 0.6143 0.01342 0.00540 -0.0510 0.6088 1.0000
3.750 0.6387 0.01363 0.00558 -0.0502 0.5854 1.0000
4.000 0.6627 0.01387 0.00579 -0.0493 0.5605 1.0000
4.250 0.6865 0.01413 0.00601 -0.0484 0.5345 1.0000
4.500 0.7100 0.01442 0.00626 -0.0474 0.5073 1.0000
4.750 0.7331 0.01474 0.00656 -0.0465 0.4788 1.0000
5.000 0.7560 0.01510 0.00687 -0.0455 0.4493 1.0000
5.250 0.7784 0.01550 0.00721 -0.0444 0.4186 1.0000
5.500 0.8003 0.01595 0.00759 -0.0434 0.3871 1.0000
5.750 0.8220 0.01644 0.00802 -0.0423 0.3536 1.0000
6.000 0.8430 0.01698 0.00852 -0.0412 0.3196 1.0000
6.250 0.8636 0.01759 0.00904 -0.0401 0.2854 1.0000
6.500 0.8838 0.01825 0.00962 -0.0390 0.2508 1.0000
6.750 0.9034 0.01898 0.01026 -0.0378 0.2185 1.0000
7.000 0.9228 0.01976 0.01098 -0.0367 0.1876 1.0000
7.250 0.9414 0.02064 0.01176 -0.0355 0.1558 1.0000
7.500 0.9591 0.02161 0.01261 -0.0343 0.1260 1.0000
7.750 0.9765 0.02263 0.01358 -0.0330 0.1011 1.0000
8.000 0.9927 0.02376 0.01461 -0.0316 0.0821 1.0000
8.250 1.0089 0.02488 0.01576 -0.0302 0.0667 1.0000
8.500 1.0228 0.02619 0.01706 -0.0285 0.0569 1.0000
8.750 1.0370 0.02746 0.01848 -0.0267 0.0496 1.0000
9.000 1.0482 0.02896 0.02003 -0.0247 0.0445 1.0000
9.250 1.0615 0.03025 0.02146 -0.0229 0.0394 1.0000
9.500 1.0706 0.03183 0.02311 -0.0209 0.0362 1.0000
9.750 1.0807 0.03348 0.02492 -0.0188 0.0342 1.0000
10.000 1.0918 0.03519 0.02683 -0.0168 0.0321 1.0000
10.250 1.1013 0.03684 0.02864 -0.0150 0.0298 1.0000
10.500 1.1078 0.03844 0.03032 -0.0131 0.0277 1.0000
10.750 1.1131 0.04080 0.03275 -0.0113 0.0261 1.0000
11.000 1.1209 0.04306 0.03532 -0.0097 0.0251 1.0000
11.250 1.1250 0.04553 0.03808 -0.0080 0.0238 1.0000
11.500 1.1260 0.04803 0.04085 -0.0065 0.0226 1.0000
11.750 1.1246 0.05057 0.04361 -0.0053 0.0215 1.0000
12.000 1.1217 0.05319 0.04639 -0.0045 0.0206 1.0000
12.250 1.1174 0.05614 0.04952 -0.0041 0.0198 1.0000
12.500 1.1112 0.05969 0.05323 -0.0041 0.0193 1.0000
12.750 1.1020 0.06389 0.05763 -0.0047 0.0190 1.0000
13.000 1.0894 0.06882 0.06278 -0.0058 0.0188 1.0000
13.250 1.0743 0.07428 0.06846 -0.0079 0.0187 1.0000
13.500 1.0592 0.08011 0.07452 -0.0107 0.0187 1.0000
13.750 1.0409 0.08689 0.08151 -0.0145 0.0186 1.0000
14.000 1.0221 0.09433 0.08915 -0.0190 0.0187 1.0000
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Polar data table (+)
Polar graphs
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