EPPLER 502 AIRFOIL (e502-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 502 AIRFOIL (e502-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.66 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e502-il-1000000.txt Download as CSV file: xf-e502-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6418 0.04868 0.04571 -0.0819 0.8026 0.0063
-12.000 -0.6568 0.04564 0.04249 -0.0805 0.7947 0.0064
-11.750 -0.7868 0.02933 0.02479 -0.0684 0.7876 0.0040
-11.500 -0.7834 0.02769 0.02292 -0.0661 0.7818 0.0039
-11.250 -0.7800 0.02583 0.02083 -0.0636 0.7764 0.0039
-11.000 -0.7706 0.02467 0.01951 -0.0617 0.7713 0.0039
-10.750 -0.7607 0.02335 0.01802 -0.0598 0.7669 0.0039
-10.500 -0.7476 0.02235 0.01690 -0.0582 0.7626 0.0038
-10.250 -0.7349 0.02122 0.01560 -0.0565 0.7587 0.0038
-10.000 -0.7244 0.01974 0.01393 -0.0544 0.7551 0.0039
-9.750 -0.7064 0.01926 0.01340 -0.0533 0.7520 0.0038
-9.500 -0.6936 0.01811 0.01212 -0.0514 0.7488 0.0039
-9.250 -0.6792 0.01726 0.01116 -0.0497 0.7456 0.0040
-9.000 -0.6647 0.01647 0.01027 -0.0478 0.7424 0.0042
-8.750 -0.6481 0.01590 0.00962 -0.0463 0.7395 0.0043
-8.500 -0.6311 0.01534 0.00900 -0.0448 0.7369 0.0042
-8.250 -0.6143 0.01478 0.00840 -0.0433 0.7342 0.0046
-8.000 -0.5970 0.01430 0.00784 -0.0417 0.7317 0.0046
-7.750 -0.5800 0.01383 0.00731 -0.0400 0.7292 0.0050
-7.500 -0.5626 0.01346 0.00686 -0.0384 0.7266 0.0054
-7.250 -0.5480 0.01294 0.00628 -0.0361 0.7244 0.0065
-7.000 -0.5309 0.01258 0.00591 -0.0343 0.7220 0.0078
-6.750 -0.5129 0.01217 0.00551 -0.0327 0.7198 0.0108
-6.500 -0.4923 0.01188 0.00525 -0.0317 0.7177 0.0169
-6.250 -0.4709 0.01161 0.00497 -0.0307 0.7156 0.0207
-6.000 -0.4482 0.01143 0.00477 -0.0300 0.7135 0.0235
-5.750 -0.4255 0.01123 0.00454 -0.0293 0.7114 0.0265
-5.500 -0.4031 0.01097 0.00431 -0.0285 0.7095 0.0309
-5.250 -0.3800 0.01075 0.00411 -0.0279 0.7075 0.0372
-5.000 -0.3570 0.01052 0.00389 -0.0272 0.7056 0.0450
-4.750 -0.3358 0.01018 0.00365 -0.0263 0.7037 0.0642
-4.500 -0.3152 0.00982 0.00341 -0.0252 0.7019 0.0964
-4.250 -0.2966 0.00936 0.00316 -0.0238 0.6999 0.1511
-4.000 -0.2794 0.00885 0.00292 -0.0222 0.6977 0.2262
-3.750 -0.2648 0.00811 0.00262 -0.0201 0.6961 0.3331
-3.500 -0.2543 0.00713 0.00222 -0.0174 0.6943 0.4827
-3.250 -0.2433 0.00627 0.00200 -0.0144 0.6924 0.6473
-3.000 -0.2163 0.00626 0.00202 -0.0143 0.6906 0.6812
-2.750 -0.1882 0.00629 0.00201 -0.0144 0.6888 0.6950
-2.500 -0.1601 0.00634 0.00203 -0.0146 0.6870 0.7062
-2.250 -0.1319 0.00643 0.00208 -0.0147 0.6852 0.7167
-2.000 -0.1037 0.00657 0.00216 -0.0149 0.6833 0.7253
-1.750 -0.0755 0.00666 0.00229 -0.0150 0.6818 0.7354
-1.500 -0.0473 0.00674 0.00237 -0.0151 0.6801 0.7432
-1.250 -0.0186 0.00685 0.00249 -0.0153 0.6782 0.7496
-1.000 0.0098 0.00695 0.00255 -0.0155 0.6764 0.7547
-0.750 0.0388 0.00694 0.00255 -0.0159 0.6746 0.7579
-0.500 0.0679 0.00694 0.00253 -0.0163 0.6728 0.7596
-0.250 0.0970 0.00696 0.00251 -0.0168 0.6709 0.7607
0.000 0.1261 0.00699 0.00251 -0.0173 0.6688 0.7617
0.250 0.1550 0.00696 0.00249 -0.0177 0.6670 0.7626
0.500 0.1839 0.00694 0.00247 -0.0182 0.6646 0.7637
0.750 0.2128 0.00692 0.00243 -0.0186 0.6618 0.7647
1.000 0.2417 0.00691 0.00240 -0.0191 0.6592 0.7656
1.250 0.2707 0.00692 0.00237 -0.0195 0.6565 0.7664
1.500 0.2994 0.00693 0.00238 -0.0199 0.6535 0.7672
1.750 0.3281 0.00690 0.00236 -0.0203 0.6502 0.7680
2.000 0.3568 0.00687 0.00233 -0.0207 0.6469 0.7690
2.250 0.3854 0.00683 0.00230 -0.0211 0.6437 0.7701
2.500 0.4141 0.00684 0.00230 -0.0215 0.6401 0.7710
2.750 0.4425 0.00680 0.00230 -0.0219 0.6363 0.7719
3.000 0.4710 0.00677 0.00231 -0.0222 0.6323 0.7728
3.250 0.4995 0.00678 0.00231 -0.0226 0.6284 0.7737
3.500 0.5277 0.00678 0.00234 -0.0229 0.6239 0.7747
3.750 0.5560 0.00676 0.00236 -0.0232 0.6183 0.7757
4.000 0.5838 0.00678 0.00237 -0.0234 0.6126 0.7767
4.250 0.6119 0.00676 0.00241 -0.0237 0.6057 0.7779
4.500 0.6394 0.00680 0.00244 -0.0239 0.5988 0.7791
4.750 0.6674 0.00681 0.00250 -0.0241 0.5906 0.7803
5.000 0.6945 0.00685 0.00255 -0.0242 0.5801 0.7813
5.250 0.7210 0.00691 0.00261 -0.0242 0.5663 0.7823
5.500 0.7459 0.00703 0.00268 -0.0239 0.5442 0.7834
5.750 0.7690 0.00721 0.00280 -0.0233 0.5151 0.7848
6.000 0.7872 0.00762 0.00303 -0.0217 0.4658 0.7862
6.250 0.8015 0.00821 0.00339 -0.0196 0.4088 0.7877
6.500 0.8170 0.00873 0.00373 -0.0177 0.3643 0.7892
6.750 0.8313 0.00927 0.00410 -0.0155 0.3211 0.7909
7.000 0.8423 0.00989 0.00451 -0.0129 0.2748 0.7927
7.250 0.8529 0.01046 0.00491 -0.0101 0.2351 0.7946
7.500 0.8598 0.01100 0.00529 -0.0066 0.2020 0.7965
7.750 0.8648 0.01151 0.00569 -0.0027 0.1738 0.7989
8.000 0.8688 0.01215 0.00621 0.0011 0.1440 0.8014
8.250 0.8741 0.01282 0.00678 0.0045 0.1195 0.8039
8.500 0.8806 0.01352 0.00738 0.0075 0.0975 0.8065
8.750 0.8858 0.01433 0.00808 0.0104 0.0755 0.8093
9.000 0.8947 0.01506 0.00875 0.0127 0.0612 0.8119
9.250 0.9029 0.01584 0.00949 0.0150 0.0479 0.8151
9.500 0.9133 0.01657 0.01022 0.0169 0.0387 0.8183
9.750 0.9247 0.01731 0.01095 0.0185 0.0318 0.8218
10.250 0.9480 0.01880 0.01247 0.0216 0.0218 0.8294
10.500 0.9581 0.01966 0.01333 0.0233 0.0166 0.8341
10.750 0.9680 0.02056 0.01422 0.0248 0.0124 0.8393
11.000 0.9775 0.02147 0.01518 0.0265 0.0095 0.8455
11.250 0.9861 0.02247 0.01623 0.0281 0.0070 0.8527
11.500 0.9946 0.02346 0.01730 0.0298 0.0060 0.8615
11.750 1.0024 0.02449 0.01845 0.0315 0.0048 0.8734
12.000 1.0116 0.02536 0.01946 0.0331 0.0047 0.8927
12.250 1.0278 0.02649 0.02082 0.0327 0.0039 0.9402
12.500 1.0639 0.02865 0.02315 0.0267 0.0033 0.9854
12.750 1.0699 0.03007 0.02462 0.0281 0.0034 1.0000
13.000 1.0795 0.03130 0.02591 0.0290 0.0030 1.0000
13.250 1.0867 0.03275 0.02742 0.0300 0.0029 1.0000
13.500 1.0920 0.03439 0.02915 0.0310 0.0029 1.0000
13.750 1.0971 0.03610 0.03093 0.0319 0.0028 1.0000
14.000 1.0998 0.03806 0.03298 0.0329 0.0026 1.0000
14.250 1.1046 0.03991 0.03490 0.0336 0.0026 1.0000
14.500 1.1093 0.04179 0.03688 0.0342 0.0027 1.0000
14.750 1.1117 0.04395 0.03912 0.0348 0.0026 1.0000
15.000 1.1120 0.04640 0.04165 0.0353 0.0025 1.0000
15.250 1.1119 0.04897 0.04433 0.0357 0.0025 1.0000
15.500 1.1117 0.05160 0.04705 0.0359 0.0025 1.0000
15.750 1.1108 0.05442 0.04997 0.0360 0.0025 1.0000
16.000 1.1104 0.05726 0.05290 0.0359 0.0024 1.0000
16.250 1.1061 0.06067 0.05643 0.0357 0.0024 1.0000
16.500 1.0996 0.06444 0.06032 0.0353 0.0024 1.0000
16.750 1.0972 0.06786 0.06383 0.0346 0.0024 1.0000
17.000 1.0880 0.07227 0.06838 0.0337 0.0024 1.0000
17.250 1.0830 0.07628 0.07250 0.0326 0.0024 1.0000
17.500 1.0796 0.08020 0.07650 0.0313 0.0023 1.0000
17.750 1.0705 0.08507 0.08153 0.0297 0.0024 1.0000
18.000 1.0609 0.09022 0.08679 0.0277 0.0023 1.0000
18.250 1.0546 0.09498 0.09167 0.0256 0.0024 1.0000
18.500 1.0367 0.10176 0.09862 0.0228 0.0024 1.0000
18.750 1.0295 0.10705 0.10400 0.0202 0.0024 1.0000
19.000 1.0171 0.11333 0.11041 0.0171 0.0024 1.0000
19.250 1.0036 0.12000 0.11720 0.0137 0.0023 1.0000
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Polar data table (+)
Polar graphs
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