E224 (10.17%) (e224-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: E224 (10.17%) (e224-il) Reynolds number: 200,000 Max Cl/Cd: 68.25 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e224-il-200000.txt Download as CSV file: xf-e224-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.6126 0.03989 0.03495 -0.0449 1.0000 0.0292
-7.250 -0.6119 0.03503 0.02983 -0.0429 1.0000 0.0278
-7.000 -0.6052 0.03137 0.02577 -0.0407 1.0000 0.0270
-6.750 -0.5941 0.02828 0.02225 -0.0386 1.0000 0.0266
-6.500 -0.5793 0.02598 0.01957 -0.0368 1.0000 0.0269
-6.250 -0.5622 0.02429 0.01757 -0.0352 1.0000 0.0279
-6.000 -0.5433 0.02337 0.01636 -0.0336 1.0000 0.0293
-5.750 -0.5241 0.02139 0.01411 -0.0322 1.0000 0.0297
-5.500 -0.5047 0.01913 0.01172 -0.0309 1.0000 0.0310
-5.250 -0.4847 0.01792 0.01050 -0.0297 1.0000 0.0333
-5.000 -0.4640 0.01706 0.00956 -0.0286 1.0000 0.0367
-4.750 -0.4436 0.01607 0.00856 -0.0276 1.0000 0.0433
-4.500 -0.4214 0.01521 0.00767 -0.0269 0.9998 0.0531
-4.250 -0.3828 0.01406 0.00673 -0.0296 0.9955 0.0954
-4.000 -0.3456 0.01314 0.00625 -0.0323 0.9906 0.1851
-3.750 -0.3068 0.01263 0.00606 -0.0352 0.9854 0.2669
-3.500 -0.2694 0.01225 0.00592 -0.0376 0.9799 0.3447
-3.250 -0.2318 0.01191 0.00581 -0.0399 0.9737 0.4163
-3.000 -0.1926 0.01164 0.00573 -0.0424 0.9685 0.4801
-2.750 -0.1577 0.01139 0.00561 -0.0439 0.9610 0.5369
-2.500 -0.1163 0.01115 0.00553 -0.0465 0.9565 0.5940
-2.250 -0.0843 0.01094 0.00545 -0.0472 0.9479 0.6422
-2.000 -0.0435 0.01073 0.00535 -0.0494 0.9433 0.6909
-1.750 -0.0106 0.01056 0.00529 -0.0500 0.9353 0.7321
-1.500 0.0285 0.01037 0.00517 -0.0518 0.9302 0.7715
-1.250 0.0607 0.01022 0.00508 -0.0520 0.9224 0.8063
-1.000 0.0947 0.01005 0.00495 -0.0525 0.9156 0.8391
-0.750 0.1229 0.00993 0.00487 -0.0517 0.9061 0.8697
-0.500 0.1563 0.00976 0.00470 -0.0519 0.8993 0.8977
-0.250 0.1861 0.00966 0.00460 -0.0514 0.8881 0.9237
0.000 0.2246 0.00956 0.00446 -0.0529 0.8782 0.9457
0.250 0.2708 0.00942 0.00427 -0.0561 0.8693 0.9619
0.500 0.3183 0.00930 0.00411 -0.0598 0.8572 0.9758
0.750 0.3677 0.00918 0.00394 -0.0640 0.8437 0.9874
1.000 0.4167 0.00905 0.00376 -0.0683 0.8289 0.9995
1.250 0.4373 0.00901 0.00363 -0.0669 0.8120 1.0000
1.500 0.4560 0.00902 0.00359 -0.0651 0.7933 1.0000
1.750 0.4762 0.00905 0.00356 -0.0635 0.7750 1.0000
2.000 0.4976 0.00911 0.00354 -0.0621 0.7570 1.0000
2.250 0.5194 0.00919 0.00355 -0.0608 0.7381 1.0000
2.500 0.5416 0.00929 0.00359 -0.0595 0.7179 1.0000
2.750 0.5647 0.00942 0.00364 -0.0583 0.6981 1.0000
3.000 0.5879 0.00955 0.00372 -0.0573 0.6764 1.0000
3.250 0.6117 0.00971 0.00379 -0.0563 0.6548 1.0000
3.500 0.6353 0.00987 0.00391 -0.0553 0.6313 1.0000
3.750 0.6591 0.01007 0.00405 -0.0543 0.6073 1.0000
4.000 0.6828 0.01028 0.00418 -0.0534 0.5822 1.0000
4.250 0.7064 0.01051 0.00435 -0.0524 0.5554 1.0000
4.500 0.7299 0.01076 0.00456 -0.0515 0.5277 1.0000
4.750 0.7531 0.01105 0.00477 -0.0505 0.4987 1.0000
5.000 0.7760 0.01137 0.00500 -0.0495 0.4680 1.0000
5.250 0.7985 0.01172 0.00527 -0.0485 0.4352 1.0000
5.500 0.8209 0.01210 0.00559 -0.0475 0.4016 1.0000
5.750 0.8428 0.01254 0.00593 -0.0465 0.3677 1.0000
6.000 0.8645 0.01301 0.00630 -0.0454 0.3314 1.0000
6.250 0.8853 0.01357 0.00673 -0.0443 0.2937 1.0000
6.500 0.9053 0.01421 0.00719 -0.0432 0.2508 1.0000
6.750 0.9249 0.01493 0.00774 -0.0420 0.2080 1.0000
7.000 0.9445 0.01569 0.00835 -0.0409 0.1701 1.0000
7.250 0.9635 0.01654 0.00905 -0.0397 0.1362 1.0000
7.500 0.9817 0.01749 0.00985 -0.0384 0.1057 1.0000
7.750 0.9981 0.01863 0.01088 -0.0368 0.0796 1.0000
8.000 1.0114 0.02009 0.01219 -0.0347 0.0610 1.0000
8.250 1.0250 0.02151 0.01361 -0.0327 0.0502 1.0000
8.500 1.0426 0.02258 0.01480 -0.0311 0.0448 1.0000
8.750 1.0562 0.02411 0.01631 -0.0292 0.0402 1.0000
9.000 1.0729 0.02547 0.01780 -0.0277 0.0367 1.0000
9.250 1.0900 0.02683 0.01927 -0.0262 0.0338 1.0000
9.500 1.1060 0.02833 0.02079 -0.0248 0.0314 1.0000
9.750 1.1222 0.03092 0.02353 -0.0236 0.0290 1.0000
10.000 1.1385 0.03249 0.02535 -0.0221 0.0274 1.0000
10.250 1.1537 0.03454 0.02763 -0.0206 0.0260 1.0000
10.500 1.1663 0.03675 0.03007 -0.0189 0.0249 1.0000
10.750 1.1756 0.03867 0.03216 -0.0170 0.0237 1.0000
11.000 1.1826 0.04109 0.03469 -0.0152 0.0227 1.0000
11.250 1.1795 0.04581 0.03973 -0.0129 0.0219 1.0000
11.500 1.1701 0.04840 0.04261 -0.0096 0.0215 1.0000
11.750 1.1608 0.05091 0.04541 -0.0069 0.0213 1.0000
12.000 1.1489 0.05409 0.04886 -0.0049 0.0212 1.0000
12.250 1.1344 0.05779 0.05283 -0.0037 0.0211 1.0000
12.500 1.1182 0.06200 0.05728 -0.0034 0.0211 1.0000
12.750 1.0997 0.06675 0.06226 -0.0041 0.0211 1.0000
13.000 1.0803 0.07227 0.06798 -0.0058 0.0213 1.0000
13.250 1.0602 0.07855 0.07444 -0.0085 0.0215 1.0000
13.500 1.0385 0.08545 0.08152 -0.0123 0.0215 1.0000
13.750 0.8562 0.10303 0.09997 -0.0229 0.0263 1.0000
14.000 0.8108 0.11516 0.11221 -0.0310 0.0280 1.0000
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Polar data table (+)
Polar graphs
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