EPPLER 521 AIRFOIL (e521-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 521 AIRFOIL (e521-il) Reynolds number: 50,000 Max Cl/Cd: 29.06 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e521-il-50000-n5.txt Download as CSV file: xf-e521-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 521 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.7541 0.09960 0.09264 -0.0242 1.0000 0.0513
-13.500 -0.7768 0.09128 0.08421 -0.0292 1.0000 0.0508
-13.250 -0.8001 0.08375 0.07652 -0.0335 1.0000 0.0506
-13.000 -0.8229 0.07711 0.06967 -0.0368 1.0000 0.0505
-12.750 -0.8428 0.07147 0.06377 -0.0390 1.0000 0.0508
-12.500 -0.8611 0.06648 0.05848 -0.0403 1.0000 0.0513
-12.250 -0.8622 0.06335 0.05537 -0.0405 1.0000 0.0534
-12.000 -0.8654 0.06031 0.05224 -0.0405 1.0000 0.0555
-11.750 -0.8695 0.05702 0.04872 -0.0402 1.0000 0.0575
-11.500 -0.8713 0.05373 0.04514 -0.0395 1.0000 0.0599
-11.250 -0.8728 0.05064 0.04161 -0.0386 1.0000 0.0630
-11.000 -0.8651 0.04855 0.03956 -0.0379 1.0000 0.0673
-10.750 -0.8583 0.04632 0.03713 -0.0369 1.0000 0.0723
-10.500 -0.8452 0.04399 0.03457 -0.0360 1.0000 0.0779
-10.250 -0.8366 0.04224 0.03278 -0.0349 1.0000 0.0848
-10.000 -0.8246 0.04041 0.03086 -0.0338 1.0000 0.0929
-9.750 -0.8116 0.03871 0.02897 -0.0327 1.0000 0.1029
-9.500 -0.8016 0.03722 0.02750 -0.0314 1.0000 0.1138
-9.250 -0.7895 0.03575 0.02604 -0.0301 1.0000 0.1262
-9.000 -0.7790 0.03442 0.02470 -0.0286 1.0000 0.1405
-8.750 -0.7684 0.03317 0.02343 -0.0269 1.0000 0.1566
-8.500 -0.7591 0.03201 0.02230 -0.0250 1.0000 0.1739
-8.250 -0.7500 0.03094 0.02130 -0.0230 1.0000 0.1926
-8.000 -0.7419 0.02997 0.02035 -0.0208 1.0000 0.2135
-7.750 -0.7363 0.02909 0.01959 -0.0180 1.0000 0.2337
-7.500 -0.7337 0.02836 0.01892 -0.0146 1.0000 0.2545
-7.250 -0.7332 0.02770 0.01835 -0.0107 1.0000 0.2755
-7.000 -0.7325 0.02709 0.01780 -0.0068 1.0000 0.2974
-6.750 -0.7311 0.02647 0.01727 -0.0030 1.0000 0.3217
-6.500 -0.7279 0.02588 0.01674 0.0007 1.0000 0.3484
-6.250 -0.7230 0.02531 0.01623 0.0041 1.0000 0.3777
-6.000 -0.7162 0.02479 0.01582 0.0074 1.0000 0.4099
-5.750 -0.7076 0.02435 0.01550 0.0105 1.0000 0.4447
-5.500 -0.6966 0.02407 0.01535 0.0135 1.0000 0.4810
-5.250 -0.6785 0.02398 0.01534 0.0154 0.9980 0.5204
-5.000 -0.6489 0.02430 0.01572 0.0157 0.9929 0.5601
-4.750 -0.6204 0.02469 0.01603 0.0162 0.9878 0.5950
-4.500 -0.5894 0.02522 0.01645 0.0163 0.9828 0.6253
-4.250 -0.5621 0.02564 0.01671 0.0167 0.9773 0.6521
-4.000 -0.5323 0.02618 0.01709 0.0170 0.9721 0.6745
-3.750 -0.5022 0.02660 0.01731 0.0168 0.9671 0.6962
-3.500 -0.4751 0.02702 0.01758 0.0173 0.9615 0.7143
-3.250 -0.4445 0.02737 0.01777 0.0170 0.9564 0.7324
-3.000 -0.4177 0.02760 0.01783 0.0172 0.9509 0.7498
-2.750 -0.3912 0.02779 0.01790 0.0175 0.9449 0.7659
-2.500 -0.3551 0.02810 0.01807 0.0162 0.9405 0.7796
-2.250 -0.3254 0.02832 0.01817 0.0160 0.9348 0.7922
-2.000 -0.2904 0.02852 0.01827 0.0148 0.9295 0.8040
-1.750 -0.2496 0.02869 0.01834 0.0123 0.9253 0.8153
-1.500 -0.2253 0.02873 0.01829 0.0127 0.9180 0.8272
-1.250 -0.1900 0.02878 0.01826 0.0110 0.9125 0.8386
-1.000 -0.1476 0.02893 0.01836 0.0082 0.9072 0.8465
-0.750 -0.1134 0.02896 0.01833 0.0066 0.9005 0.8561
-0.500 -0.0699 0.02900 0.01833 0.0034 0.8953 0.8643
-0.250 -0.0374 0.02903 0.01835 0.0022 0.8872 0.8724
0.000 0.0003 0.02901 0.01831 -0.0001 0.8810 0.8808
0.250 0.0375 0.02903 0.01835 -0.0022 0.8724 0.8873
0.500 0.0701 0.02900 0.01833 -0.0034 0.8644 0.8953
0.750 0.1134 0.02896 0.01833 -0.0066 0.8561 0.9005
1.000 0.1476 0.02893 0.01835 -0.0082 0.8465 0.9072
1.250 0.1898 0.02878 0.01827 -0.0109 0.8387 0.9125
1.500 0.2252 0.02873 0.01829 -0.0127 0.8272 0.9180
1.750 0.2495 0.02869 0.01833 -0.0123 0.8153 0.9253
2.000 0.2904 0.02852 0.01827 -0.0148 0.8040 0.9295
2.250 0.3253 0.02832 0.01817 -0.0160 0.7921 0.9348
2.500 0.3552 0.02809 0.01807 -0.0162 0.7797 0.9405
2.750 0.3912 0.02779 0.01790 -0.0175 0.7658 0.9449
3.000 0.4177 0.02759 0.01783 -0.0172 0.7498 0.9509
3.250 0.4447 0.02736 0.01777 -0.0171 0.7324 0.9564
3.500 0.4752 0.02701 0.01758 -0.0174 0.7143 0.9615
3.750 0.5023 0.02660 0.01731 -0.0168 0.6962 0.9671
4.000 0.5324 0.02618 0.01709 -0.0170 0.6745 0.9721
4.250 0.5621 0.02564 0.01671 -0.0168 0.6521 0.9773
4.500 0.5894 0.02522 0.01645 -0.0163 0.6254 0.9828
4.750 0.6204 0.02469 0.01603 -0.0162 0.5951 0.9877
5.000 0.6489 0.02429 0.01571 -0.0157 0.5601 0.9929
5.250 0.6786 0.02398 0.01534 -0.0154 0.5205 0.9980
5.500 0.6967 0.02407 0.01534 -0.0135 0.4809 1.0000
5.750 0.7077 0.02435 0.01550 -0.0105 0.4447 1.0000
6.000 0.7164 0.02479 0.01582 -0.0074 0.4099 1.0000
6.250 0.7231 0.02531 0.01623 -0.0041 0.3778 1.0000
6.500 0.7279 0.02588 0.01674 -0.0007 0.3482 1.0000
6.750 0.7311 0.02647 0.01726 0.0029 0.3215 1.0000
7.000 0.7327 0.02708 0.01779 0.0068 0.2975 1.0000
7.250 0.7332 0.02770 0.01834 0.0107 0.2755 1.0000
7.500 0.7338 0.02836 0.01892 0.0146 0.2546 1.0000
7.750 0.7364 0.02909 0.01959 0.0180 0.2337 1.0000
8.000 0.7419 0.02996 0.02034 0.0208 0.2137 1.0000
8.250 0.7499 0.03093 0.02130 0.0231 0.1927 1.0000
8.500 0.7590 0.03201 0.02230 0.0250 0.1740 1.0000
8.750 0.7683 0.03316 0.02342 0.0269 0.1567 1.0000
9.000 0.7788 0.03441 0.02468 0.0286 0.1405 1.0000
9.250 0.7892 0.03574 0.02603 0.0301 0.1261 1.0000
9.500 0.8015 0.03721 0.02749 0.0314 0.1138 1.0000
9.750 0.8119 0.03869 0.02896 0.0327 0.1031 1.0000
10.000 0.8248 0.04039 0.03084 0.0338 0.0930 1.0000
10.250 0.8366 0.04222 0.03276 0.0349 0.0848 1.0000
10.500 0.8451 0.04398 0.03455 0.0360 0.0778 1.0000
10.750 0.8582 0.04632 0.03713 0.0369 0.0722 1.0000
11.000 0.8651 0.04853 0.03953 0.0379 0.0673 1.0000
11.250 0.8729 0.05062 0.04159 0.0386 0.0630 1.0000
11.500 0.8713 0.05372 0.04512 0.0395 0.0598 1.0000
11.750 0.8696 0.05701 0.04872 0.0402 0.0574 1.0000
12.000 0.8656 0.06027 0.05218 0.0405 0.0554 1.0000
12.250 0.8628 0.06326 0.05527 0.0405 0.0533 1.0000
12.500 0.8620 0.06639 0.05838 0.0403 0.0513 1.0000
12.750 0.8433 0.07143 0.06374 0.0390 0.0508 1.0000
13.000 0.8227 0.07717 0.06973 0.0368 0.0505 1.0000
13.250 0.8006 0.08375 0.07652 0.0335 0.0506 1.0000
13.500 0.7773 0.09129 0.08421 0.0292 0.0509 1.0000
13.750 0.7523 0.10006 0.09310 0.0238 0.0512 1.0000
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