E224 (10.17%) (e224-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E224 (10.17%) (e224-il) Reynolds number: 500,000 Max Cl/Cd: 89.22 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e224-il-500000.txt Download as CSV file: xf-e224-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5096 0.09225 0.08996 -0.0314 1.0000 0.0219
-10.250 -0.5184 0.08577 0.08351 -0.0345 1.0000 0.0220
-10.000 -0.5286 0.08000 0.07777 -0.0372 1.0000 0.0225
-7.750 -0.6835 0.02512 0.02047 -0.0395 1.0000 0.0119
-7.500 -0.6691 0.02335 0.01838 -0.0375 0.9999 0.0115
-7.250 -0.6374 0.02130 0.01602 -0.0391 0.9976 0.0114
-7.000 -0.6072 0.01858 0.01302 -0.0405 0.9954 0.0116
-6.750 -0.5755 0.01695 0.01125 -0.0419 0.9931 0.0122
-6.500 -0.5432 0.01590 0.01012 -0.0432 0.9900 0.0129
-6.250 -0.5095 0.01490 0.00902 -0.0448 0.9871 0.0135
-6.000 -0.4739 0.01411 0.00811 -0.0466 0.9848 0.0146
-5.750 -0.4373 0.01354 0.00747 -0.0486 0.9828 0.0156
-5.500 -0.4084 0.01237 0.00623 -0.0493 0.9776 0.0181
-5.250 -0.3731 0.01180 0.00560 -0.0509 0.9743 0.0211
-5.000 -0.3367 0.01102 0.00475 -0.0529 0.9719 0.0293
-4.750 -0.2996 0.01021 0.00411 -0.0551 0.9702 0.0604
-4.500 -0.2702 0.00967 0.00375 -0.0556 0.9640 0.1016
-4.250 -0.2350 0.00914 0.00343 -0.0575 0.9607 0.1517
-4.000 -0.1995 0.00865 0.00315 -0.0594 0.9576 0.2080
-3.750 -0.1688 0.00827 0.00292 -0.0601 0.9517 0.2563
-3.500 -0.1370 0.00790 0.00270 -0.0609 0.9456 0.3053
-3.250 -0.1059 0.00755 0.00251 -0.0617 0.9394 0.3600
-3.000 -0.0770 0.00727 0.00235 -0.0618 0.9310 0.4036
-2.750 -0.0483 0.00703 0.00221 -0.0619 0.9223 0.4439
-2.500 -0.0193 0.00682 0.00208 -0.0620 0.9137 0.4837
-2.250 0.0073 0.00664 0.00198 -0.0616 0.9024 0.5232
-2.000 0.0343 0.00649 0.00190 -0.0613 0.8914 0.5606
-1.750 0.0612 0.00635 0.00183 -0.0609 0.8800 0.5972
-1.500 0.0881 0.00624 0.00177 -0.0604 0.8683 0.6313
-1.250 0.1147 0.00616 0.00172 -0.0600 0.8559 0.6643
-0.750 0.1674 0.00603 0.00167 -0.0589 0.8291 0.7251
-0.500 0.1935 0.00599 0.00166 -0.0583 0.8154 0.7536
-0.250 0.2195 0.00596 0.00166 -0.0576 0.8012 0.7810
0.000 0.2452 0.00594 0.00167 -0.0569 0.7866 0.8074
0.250 0.2705 0.00594 0.00169 -0.0560 0.7716 0.8324
0.500 0.2956 0.00596 0.00171 -0.0552 0.7561 0.8569
0.750 0.3201 0.00599 0.00173 -0.0541 0.7404 0.8796
1.000 0.3443 0.00602 0.00176 -0.0530 0.7240 0.9019
1.250 0.3683 0.00606 0.00178 -0.0518 0.7070 0.9237
1.500 0.3940 0.00611 0.00180 -0.0511 0.6893 0.9448
1.750 0.4250 0.00618 0.00182 -0.0515 0.6705 0.9629
2.000 0.4610 0.00628 0.00185 -0.0532 0.6500 0.9773
2.250 0.4992 0.00639 0.00189 -0.0554 0.6279 0.9884
2.500 0.5383 0.00651 0.00193 -0.0579 0.6047 0.9979
2.750 0.5634 0.00666 0.00200 -0.0575 0.5825 1.0000
3.000 0.5856 0.00682 0.00207 -0.0564 0.5597 1.0000
3.250 0.6087 0.00700 0.00217 -0.0554 0.5363 1.0000
3.500 0.6326 0.00720 0.00228 -0.0547 0.5119 1.0000
3.750 0.6569 0.00741 0.00241 -0.0540 0.4865 1.0000
4.000 0.6813 0.00764 0.00256 -0.0534 0.4598 1.0000
4.250 0.7057 0.00791 0.00271 -0.0527 0.4301 1.0000
4.500 0.7300 0.00820 0.00290 -0.0521 0.3996 1.0000
4.750 0.7546 0.00849 0.00310 -0.0516 0.3721 1.0000
5.000 0.7789 0.00881 0.00332 -0.0510 0.3419 1.0000
5.250 0.8028 0.00919 0.00357 -0.0504 0.3089 1.0000
5.500 0.8266 0.00959 0.00385 -0.0498 0.2739 1.0000
5.750 0.8496 0.01009 0.00416 -0.0491 0.2343 1.0000
6.000 0.8726 0.01059 0.00450 -0.0484 0.1976 1.0000
6.250 0.8957 0.01109 0.00486 -0.0478 0.1675 1.0000
6.500 0.9188 0.01159 0.00525 -0.0471 0.1400 1.0000
6.750 0.9416 0.01212 0.00567 -0.0464 0.1142 1.0000
7.000 0.9642 0.01267 0.00612 -0.0457 0.0907 1.0000
7.250 0.9864 0.01325 0.00661 -0.0449 0.0705 1.0000
7.500 1.0073 0.01396 0.00721 -0.0439 0.0499 1.0000
7.750 1.0279 0.01472 0.00790 -0.0428 0.0349 1.0000
8.000 1.0480 0.01551 0.00871 -0.0416 0.0281 1.0000
8.250 1.0692 0.01614 0.00937 -0.0406 0.0245 1.0000
8.500 1.0864 0.01717 0.01046 -0.0390 0.0215 1.0000
8.750 1.1076 0.01773 0.01110 -0.0380 0.0198 1.0000
9.000 1.1268 0.01846 0.01190 -0.0368 0.0182 1.0000
9.250 1.1417 0.01955 0.01304 -0.0350 0.0164 1.0000
9.500 1.1536 0.02090 0.01451 -0.0327 0.0153 1.0000
9.750 1.1731 0.02147 0.01518 -0.0316 0.0141 1.0000
10.000 1.1882 0.02239 0.01619 -0.0299 0.0132 1.0000
10.250 1.2013 0.02334 0.01720 -0.0280 0.0123 1.0000
10.500 1.2068 0.02474 0.01867 -0.0250 0.0116 1.0000
10.750 1.2049 0.02708 0.02118 -0.0212 0.0110 1.0000
11.000 1.2150 0.02819 0.02242 -0.0191 0.0107 1.0000
11.250 1.2232 0.02950 0.02387 -0.0169 0.0103 1.0000
11.500 1.2295 0.03102 0.02553 -0.0148 0.0100 1.0000
11.750 1.2342 0.03273 0.02738 -0.0127 0.0096 1.0000
12.000 1.2387 0.03440 0.02918 -0.0109 0.0093 1.0000
12.250 1.2426 0.03604 0.03095 -0.0094 0.0089 1.0000
12.500 1.2450 0.03795 0.03297 -0.0081 0.0086 1.0000
12.750 1.2455 0.04014 0.03525 -0.0070 0.0083 1.0000
13.000 1.2430 0.04287 0.03811 -0.0062 0.0081 1.0000
13.250 1.2388 0.04597 0.04136 -0.0057 0.0080 1.0000
13.500 1.2220 0.05101 0.04662 -0.0055 0.0078 1.0000
13.750 1.2100 0.05559 0.05141 -0.0061 0.0077 1.0000
14.000 1.1920 0.06125 0.05731 -0.0077 0.0076 1.0000
14.250 1.1827 0.06588 0.06210 -0.0096 0.0076 1.0000
14.500 1.1721 0.07104 0.06744 -0.0122 0.0075 1.0000
14.750 1.1559 0.07752 0.07410 -0.0154 0.0076 1.0000
15.000 1.1379 0.08483 0.08160 -0.0195 0.0076 1.0000
15.250 1.1215 0.09233 0.08927 -0.0241 0.0075 1.0000
15.500 1.1048 0.10034 0.09744 -0.0291 0.0075 1.0000
15.750 1.0858 0.10927 0.10652 -0.0346 0.0076 1.0000
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Polar data table (+)
Polar graphs
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