EPPLER 502 AIRFOIL (e502-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 502 AIRFOIL (e502-il) Reynolds number: 500,000 Max Cl/Cd: 80.01 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e502-il-500000-n5.txt Download as CSV file: xf-e502-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 502 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.6867 0.07766 0.07517 -0.0559 1.0000 0.0031
-14.250 -0.7143 0.06733 0.06465 -0.0629 1.0000 0.0030
-14.000 -0.7306 0.05817 0.05520 -0.0714 0.9371 0.0030
-13.750 -0.7410 0.04965 0.04616 -0.0801 0.8928 0.0030
-13.500 -0.7562 0.04583 0.04195 -0.0797 0.8542 0.0030
-13.250 -0.7696 0.04264 0.03846 -0.0783 0.8349 0.0030
-13.000 -0.7803 0.03973 0.03528 -0.0767 0.8216 0.0030
-12.750 -0.7887 0.03707 0.03234 -0.0747 0.8111 0.0030
-12.500 -0.7945 0.03458 0.02957 -0.0725 0.8022 0.0031
-12.250 -0.7923 0.03291 0.02771 -0.0708 0.7948 0.0030
-12.000 -0.7888 0.03129 0.02589 -0.0689 0.7877 0.0030
-11.750 -0.7856 0.02952 0.02387 -0.0669 0.7816 0.0031
-11.500 -0.7783 0.02813 0.02231 -0.0651 0.7758 0.0031
-11.250 -0.7706 0.02670 0.02066 -0.0632 0.7708 0.0032
-11.000 -0.7593 0.02559 0.01941 -0.0617 0.7665 0.0033
-10.750 -0.7475 0.02448 0.01815 -0.0601 0.7622 0.0033
-10.500 -0.7353 0.02341 0.01693 -0.0585 0.7581 0.0033
-10.250 -0.7211 0.02253 0.01589 -0.0571 0.7547 0.0034
-10.000 -0.7069 0.02156 0.01478 -0.0556 0.7511 0.0037
-9.750 -0.6906 0.02090 0.01403 -0.0544 0.7474 0.0035
-9.500 -0.6765 0.01996 0.01297 -0.0527 0.7439 0.0038
-9.250 -0.6610 0.01919 0.01209 -0.0513 0.7409 0.0040
-9.000 -0.6436 0.01855 0.01139 -0.0501 0.7381 0.0045
-8.750 -0.6258 0.01800 0.01077 -0.0489 0.7353 0.0046
-8.500 -0.6081 0.01743 0.01012 -0.0476 0.7325 0.0048
-8.250 -0.5901 0.01694 0.00953 -0.0463 0.7299 0.0053
-8.000 -0.5722 0.01644 0.00894 -0.0450 0.7274 0.0056
-7.750 -0.5552 0.01589 0.00835 -0.0435 0.7249 0.0065
-7.500 -0.5373 0.01543 0.00786 -0.0421 0.7222 0.0077
-7.250 -0.5195 0.01500 0.00741 -0.0406 0.7198 0.0095
-7.000 -0.5013 0.01465 0.00704 -0.0392 0.7174 0.0122
-6.750 -0.4836 0.01432 0.00671 -0.0377 0.7153 0.0152
-6.500 -0.4652 0.01406 0.00641 -0.0362 0.7133 0.0192
-6.250 -0.4459 0.01380 0.00614 -0.0349 0.7112 0.0228
-6.000 -0.4254 0.01351 0.00584 -0.0339 0.7089 0.0268
-5.750 -0.4046 0.01323 0.00557 -0.0329 0.7066 0.0313
-5.500 -0.3833 0.01296 0.00528 -0.0319 0.7045 0.0360
-5.250 -0.3622 0.01268 0.00501 -0.0309 0.7026 0.0427
-5.000 -0.3409 0.01240 0.00473 -0.0300 0.7007 0.0514
-4.750 -0.3194 0.01214 0.00447 -0.0291 0.6989 0.0634
-4.500 -0.2985 0.01183 0.00422 -0.0281 0.6971 0.0849
-4.250 -0.2789 0.01144 0.00398 -0.0269 0.6950 0.1202
-4.000 -0.2596 0.01102 0.00374 -0.0256 0.6929 0.1662
-3.750 -0.2416 0.01053 0.00347 -0.0242 0.6910 0.2281
-3.500 -0.2258 0.00992 0.00319 -0.0224 0.6891 0.3132
-3.250 -0.2131 0.00914 0.00284 -0.0200 0.6872 0.4234
-3.000 -0.2095 0.00802 0.00253 -0.0157 0.6852 0.6147
-2.750 -0.1856 0.00804 0.00267 -0.0149 0.6835 0.6792
-2.500 -0.1587 0.00811 0.00272 -0.0147 0.6818 0.7006
-2.250 -0.1318 0.00823 0.00285 -0.0145 0.6800 0.7182
-2.000 -0.1046 0.00838 0.00299 -0.0143 0.6780 0.7318
-1.750 -0.0773 0.00849 0.00306 -0.0142 0.6761 0.7414
-1.500 -0.0489 0.00857 0.00313 -0.0144 0.6741 0.7468
-1.250 -0.0205 0.00859 0.00309 -0.0147 0.6724 0.7496
-1.000 0.0080 0.00858 0.00303 -0.0150 0.6708 0.7511
-0.750 0.0366 0.00859 0.00296 -0.0154 0.6692 0.7523
-0.500 0.0650 0.00857 0.00291 -0.0158 0.6672 0.7535
-0.250 0.0935 0.00856 0.00288 -0.0162 0.6652 0.7546
0.000 0.1222 0.00854 0.00286 -0.0166 0.6631 0.7555
0.250 0.1508 0.00854 0.00284 -0.0170 0.6610 0.7563
0.500 0.1794 0.00853 0.00283 -0.0173 0.6589 0.7571
0.750 0.2081 0.00854 0.00281 -0.0177 0.6570 0.7580
1.000 0.2368 0.00856 0.00281 -0.0181 0.6551 0.7592
1.250 0.2651 0.00856 0.00283 -0.0185 0.6523 0.7603
1.500 0.2933 0.00855 0.00285 -0.0188 0.6490 0.7613
1.750 0.3215 0.00854 0.00284 -0.0191 0.6457 0.7623
2.000 0.3499 0.00854 0.00283 -0.0194 0.6425 0.7634
2.250 0.3780 0.00855 0.00284 -0.0197 0.6390 0.7644
2.500 0.4059 0.00854 0.00287 -0.0200 0.6343 0.7655
2.750 0.4339 0.00854 0.00287 -0.0202 0.6300 0.7666
3.000 0.4619 0.00856 0.00288 -0.0205 0.6259 0.7677
3.250 0.4895 0.00855 0.00293 -0.0207 0.6201 0.7688
3.500 0.5171 0.00855 0.00295 -0.0209 0.6147 0.7699
3.750 0.5446 0.00856 0.00301 -0.0210 0.6088 0.7709
4.000 0.5719 0.00857 0.00307 -0.0211 0.6018 0.7719
4.250 0.5989 0.00859 0.00312 -0.0212 0.5940 0.7730
4.500 0.6254 0.00862 0.00317 -0.0211 0.5842 0.7741
4.750 0.6515 0.00866 0.00323 -0.0210 0.5715 0.7753
5.000 0.6769 0.00873 0.00331 -0.0208 0.5560 0.7766
5.250 0.7015 0.00884 0.00341 -0.0204 0.5363 0.7780
5.500 0.7233 0.00904 0.00353 -0.0195 0.5072 0.7794
5.750 0.7411 0.00941 0.00374 -0.0179 0.4663 0.7809
6.000 0.7542 0.00997 0.00409 -0.0155 0.4168 0.7826
6.250 0.7649 0.01059 0.00451 -0.0127 0.3674 0.7843
6.500 0.7758 0.01117 0.00494 -0.0100 0.3260 0.7861
6.750 0.7855 0.01175 0.00537 -0.0072 0.2883 0.7880
7.000 0.7912 0.01231 0.00579 -0.0035 0.2526 0.7901
7.250 0.7964 0.01287 0.00624 0.0002 0.2230 0.7924
7.500 0.8037 0.01349 0.00676 0.0033 0.1976 0.7947
7.750 0.8119 0.01413 0.00733 0.0061 0.1751 0.7970
8.000 0.8180 0.01486 0.00798 0.0090 0.1495 0.7993
8.250 0.8256 0.01562 0.00867 0.0116 0.1281 0.8017
8.500 0.8325 0.01647 0.00944 0.0140 0.1070 0.8045
8.750 0.8419 0.01726 0.01019 0.0160 0.0903 0.8074
9.000 0.8516 0.01809 0.01097 0.0179 0.0752 0.8104
9.250 0.8611 0.01895 0.01179 0.0197 0.0614 0.8136
9.500 0.8707 0.01982 0.01264 0.0214 0.0495 0.8171
9.750 0.8809 0.02070 0.01353 0.0230 0.0399 0.8210
10.000 0.8913 0.02160 0.01442 0.0245 0.0322 0.8249
10.250 0.9022 0.02247 0.01531 0.0259 0.0267 0.8289
10.500 0.9123 0.02341 0.01627 0.0274 0.0204 0.8336
10.750 0.9227 0.02437 0.01723 0.0287 0.0161 0.8388
11.000 0.9335 0.02529 0.01822 0.0300 0.0134 0.8444
11.250 0.9440 0.02625 0.01924 0.0312 0.0110 0.8512
11.500 0.9535 0.02727 0.02032 0.0325 0.0091 0.8590
12.000 0.9729 0.02931 0.02257 0.0350 0.0066 0.8822
12.250 0.9817 0.03052 0.02391 0.0361 0.0055 0.9038
12.750 1.0338 0.03356 0.02727 0.0301 0.0043 1.0000
13.000 1.0419 0.03498 0.02873 0.0309 0.0037 1.0000
13.250 1.0482 0.03657 0.03039 0.0318 0.0034 1.0000
13.500 1.0549 0.03819 0.03210 0.0326 0.0034 1.0000
13.750 1.0615 0.03987 0.03387 0.0333 0.0032 1.0000
14.000 1.0667 0.04170 0.03578 0.0339 0.0027 1.0000
14.250 1.0725 0.04353 0.03772 0.0344 0.0026 1.0000
14.500 1.0774 0.04550 0.03978 0.0348 0.0029 1.0000
14.750 1.0820 0.04755 0.04192 0.0351 0.0026 1.0000
15.000 1.0846 0.04985 0.04431 0.0354 0.0024 1.0000
15.250 1.0859 0.05238 0.04694 0.0356 0.0024 1.0000
15.500 1.0861 0.05509 0.04974 0.0356 0.0023 1.0000
15.750 1.0864 0.05790 0.05267 0.0354 0.0023 1.0000
16.000 1.0838 0.06112 0.05600 0.0351 0.0022 1.0000
16.250 1.0804 0.06458 0.05957 0.0346 0.0022 1.0000
16.500 1.0666 0.06953 0.06466 0.0337 0.0020 1.0000
16.750 1.0653 0.07300 0.06825 0.0327 0.0021 1.0000
17.000 1.0578 0.07744 0.07283 0.0314 0.0020 1.0000
17.250 1.0514 0.08188 0.07739 0.0299 0.0020 1.0000
17.500 1.0467 0.08623 0.08186 0.0283 0.0020 1.0000
17.750 1.0369 0.09147 0.08723 0.0262 0.0021 1.0000
18.000 1.0289 0.09664 0.09254 0.0239 0.0020 1.0000
18.250 1.0204 0.10201 0.09803 0.0215 0.0020 1.0000
18.500 1.0089 0.10807 0.10424 0.0186 0.0020 1.0000
18.750 0.9970 0.11435 0.11064 0.0154 0.0020 1.0000
19.000 0.9864 0.12057 0.11700 0.0122 0.0020 1.0000
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Polar data table (+)
Polar graphs
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