EPPLER 403 AIRFOIL (e403-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 403 AIRFOIL (e403-il) Reynolds number: 500,000 Max Cl/Cd: 98.11 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e403-il-500000-n5.txt Download as CSV file: xf-e403-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 403 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.4467 0.07610 0.07324 -0.1149 0.9754 0.0075
-13.500 -0.4811 0.06411 0.06097 -0.1242 0.9743 0.0073
-13.250 -0.5050 0.05567 0.05224 -0.1309 0.9734 0.0072
-13.000 -0.5170 0.05135 0.04776 -0.1329 0.9702 0.0072
-12.750 -0.5219 0.04785 0.04411 -0.1349 0.9673 0.0073
-12.500 -0.5246 0.04412 0.04018 -0.1375 0.9652 0.0073
-12.250 -0.5271 0.04020 0.03601 -0.1400 0.9632 0.0074
-12.000 -0.5223 0.03725 0.03284 -0.1421 0.9616 0.0075
-11.750 -0.5148 0.03451 0.02987 -0.1439 0.9601 0.0075
-11.500 -0.5138 0.03243 0.02760 -0.1430 0.9563 0.0076
-11.250 -0.5076 0.03070 0.02569 -0.1424 0.9526 0.0076
-11.000 -0.4955 0.02898 0.02380 -0.1426 0.9501 0.0076
-10.750 -0.4806 0.02742 0.02206 -0.1428 0.9482 0.0078
-10.500 -0.4632 0.02606 0.02055 -0.1432 0.9466 0.0080
-10.250 -0.4436 0.02486 0.01921 -0.1435 0.9453 0.0080
-10.000 -0.4382 0.02408 0.01835 -0.1407 0.9408 0.0080
-9.750 -0.4244 0.02320 0.01736 -0.1396 0.9378 0.0082
-9.500 -0.4076 0.02237 0.01643 -0.1390 0.9356 0.0085
-9.250 -0.3896 0.02150 0.01549 -0.1385 0.9337 0.0086
-9.000 -0.3704 0.02072 0.01462 -0.1383 0.9321 0.0087
-8.750 -0.3568 0.02006 0.01390 -0.1369 0.9294 0.0088
-8.500 -0.3556 0.01955 0.01335 -0.1331 0.9246 0.0089
-8.250 -0.3481 0.01869 0.01246 -0.1309 0.9213 0.0091
-8.000 -0.3309 0.01788 0.01161 -0.1306 0.9191 0.0093
-7.750 -0.3103 0.01708 0.01076 -0.1310 0.9173 0.0095
-7.500 -0.2890 0.01641 0.01004 -0.1313 0.9157 0.0098
-7.250 -0.2802 0.01606 0.00967 -0.1287 0.9115 0.0102
-7.000 -0.2616 0.01559 0.00916 -0.1279 0.9086 0.0107
-6.750 -0.2386 0.01509 0.00861 -0.1280 0.9066 0.0111
-6.500 -0.2133 0.01460 0.00807 -0.1284 0.9051 0.0115
-6.250 -0.1860 0.01415 0.00756 -0.1292 0.9039 0.0119
-6.000 -0.1579 0.01360 0.00697 -0.1301 0.9028 0.0126
-5.750 -0.1284 0.01319 0.00651 -0.1312 0.9018 0.0134
-5.500 -0.1040 0.01292 0.00621 -0.1311 0.8999 0.0144
-5.250 -0.0851 0.01275 0.00601 -0.1299 0.8965 0.0156
-5.000 -0.0600 0.01243 0.00571 -0.1299 0.8941 0.0203
-4.750 -0.0323 0.01180 0.00529 -0.1310 0.8924 0.0644
-4.500 -0.0019 0.01106 0.00486 -0.1328 0.8910 0.1424
-4.250 0.0320 0.00998 0.00429 -0.1358 0.8899 0.2780
-4.000 0.0683 0.00894 0.00380 -0.1392 0.8890 0.4345
-3.750 0.1017 0.00865 0.00379 -0.1409 0.8881 0.5189
-3.500 0.1338 0.00863 0.00380 -0.1419 0.8872 0.5473
-3.250 0.1660 0.00867 0.00383 -0.1429 0.8862 0.5655
-3.000 0.1872 0.00879 0.00392 -0.1417 0.8825 0.5739
-2.750 0.2133 0.00882 0.00397 -0.1414 0.8797 0.5789
-2.500 0.2424 0.00880 0.00391 -0.1418 0.8775 0.5832
-2.250 0.2738 0.00874 0.00379 -0.1427 0.8755 0.5865
-2.000 0.3063 0.00865 0.00366 -0.1438 0.8738 0.5892
-1.750 0.3396 0.00855 0.00354 -0.1450 0.8720 0.5914
-1.500 0.3619 0.00856 0.00357 -0.1439 0.8669 0.5938
-1.250 0.3900 0.00849 0.00348 -0.1440 0.8625 0.5964
-1.000 0.4221 0.00837 0.00333 -0.1450 0.8591 0.5989
-0.750 0.4525 0.00829 0.00322 -0.1455 0.8554 0.6016
-0.500 0.4762 0.00829 0.00321 -0.1448 0.8494 0.6040
-0.250 0.5057 0.00821 0.00315 -0.1452 0.8452 0.6058
0.000 0.5371 0.00814 0.00308 -0.1460 0.8417 0.6079
0.250 0.5597 0.00818 0.00315 -0.1450 0.8353 0.6101
0.500 0.5893 0.00813 0.00310 -0.1454 0.8304 0.6124
0.750 0.6167 0.00811 0.00309 -0.1454 0.8243 0.6147
1.000 0.6442 0.00808 0.00307 -0.1454 0.8168 0.6171
1.250 0.6716 0.00806 0.00303 -0.1454 0.8076 0.6195
1.500 0.7003 0.00802 0.00299 -0.1456 0.7967 0.6212
1.750 0.7283 0.00800 0.00297 -0.1456 0.7836 0.6230
2.000 0.7553 0.00803 0.00298 -0.1454 0.7679 0.6250
2.250 0.7817 0.00809 0.00299 -0.1452 0.7473 0.6272
2.500 0.8065 0.00822 0.00302 -0.1445 0.7200 0.6295
2.750 0.8271 0.00846 0.00310 -0.1430 0.6842 0.6317
3.000 0.8425 0.00883 0.00326 -0.1405 0.6424 0.6337
3.250 0.8527 0.00926 0.00347 -0.1369 0.5991 0.6356
3.500 0.8621 0.00971 0.00376 -0.1333 0.5569 0.6375
3.750 0.8743 0.01017 0.00407 -0.1303 0.5191 0.6395
4.000 0.8895 0.01062 0.00439 -0.1280 0.4853 0.6415
4.250 0.9058 0.01107 0.00471 -0.1260 0.4539 0.6436
4.500 0.9228 0.01152 0.00505 -0.1241 0.4223 0.6457
4.750 0.9402 0.01199 0.00539 -0.1224 0.3905 0.6478
5.000 0.9551 0.01261 0.00579 -0.1203 0.3483 0.6499
5.250 0.9697 0.01331 0.00624 -0.1182 0.2983 0.6519
5.500 0.9858 0.01395 0.00669 -0.1164 0.2551 0.6538
5.750 1.0041 0.01450 0.00711 -0.1150 0.2234 0.6557
6.000 1.0223 0.01508 0.00756 -0.1136 0.1932 0.6577
6.250 1.0399 0.01572 0.00804 -0.1122 0.1596 0.6597
6.500 1.0578 0.01635 0.00854 -0.1108 0.1303 0.6618
6.750 1.0760 0.01697 0.00905 -0.1095 0.1069 0.6639
7.000 1.0932 0.01767 0.00961 -0.1080 0.0818 0.6661
7.250 1.1103 0.01838 0.01020 -0.1066 0.0599 0.6682
7.500 1.1268 0.01913 0.01087 -0.1051 0.0401 0.6701
7.750 1.1437 0.01986 0.01155 -0.1036 0.0258 0.6722
8.000 1.1600 0.02064 0.01228 -0.1021 0.0154 0.6742
8.250 1.1776 0.02131 0.01297 -0.1007 0.0127 0.6764
8.500 1.1962 0.02191 0.01363 -0.0996 0.0117 0.6786
8.750 1.2139 0.02259 0.01435 -0.0983 0.0107 0.6809
9.000 1.2305 0.02335 0.01517 -0.0969 0.0099 0.6831
9.250 1.2472 0.02408 0.01598 -0.0955 0.0096 0.6853
9.500 1.2641 0.02480 0.01679 -0.0942 0.0093 0.6875
9.750 1.2799 0.02560 0.01768 -0.0927 0.0090 0.6897
10.000 1.2952 0.02645 0.01862 -0.0913 0.0087 0.6920
10.250 1.3097 0.02736 0.01961 -0.0898 0.0085 0.6944
10.500 1.3232 0.02836 0.02068 -0.0882 0.0083 0.6967
10.750 1.3360 0.02941 0.02182 -0.0865 0.0081 0.6990
11.000 1.3479 0.03055 0.02305 -0.0849 0.0079 0.7013
11.250 1.3583 0.03180 0.02440 -0.0831 0.0077 0.7038
11.500 1.3671 0.03321 0.02591 -0.0812 0.0076 0.7063
11.750 1.3737 0.03483 0.02763 -0.0792 0.0074 0.7088
12.000 1.3769 0.03677 0.02967 -0.0770 0.0072 0.7112
12.250 1.3862 0.03823 0.03123 -0.0755 0.0071 0.7136
12.500 1.3943 0.03982 0.03293 -0.0740 0.0070 0.7159
12.750 1.4013 0.04154 0.03478 -0.0725 0.0069 0.7185
13.000 1.4072 0.04341 0.03677 -0.0710 0.0067 0.7213
13.250 1.4121 0.04545 0.03894 -0.0697 0.0066 0.7243
13.500 1.4157 0.04769 0.04131 -0.0684 0.0065 0.7272
14.000 1.4212 0.05259 0.04647 -0.0662 0.0064 0.7325
14.250 1.4227 0.05530 0.04932 -0.0654 0.0063 0.7353
14.500 1.4233 0.05823 0.05239 -0.0647 0.0062 0.7383
14.750 1.4233 0.06135 0.05564 -0.0643 0.0061 0.7413
15.000 1.4225 0.06468 0.05911 -0.0641 0.0061 0.7444
15.250 1.4210 0.06822 0.06280 -0.0641 0.0060 0.7475
15.500 1.4185 0.07205 0.06678 -0.0644 0.0060 0.7509
15.750 1.4153 0.07612 0.07100 -0.0650 0.0059 0.7545
16.000 1.4112 0.08046 0.07549 -0.0660 0.0058 0.7581
16.250 1.4065 0.08506 0.08024 -0.0672 0.0058 0.7615
16.500 1.4007 0.08996 0.08531 -0.0687 0.0058 0.7649
16.750 1.3943 0.09511 0.09062 -0.0706 0.0057 0.7686
17.000 1.3875 0.10050 0.09617 -0.0728 0.0057 0.7723
17.500 1.3720 0.11200 0.10799 -0.0782 0.0056 0.7798
17.750 1.3635 0.11808 0.11422 -0.0813 0.0056 0.7839
18.000 1.3546 0.12435 0.12066 -0.0847 0.0056 0.7882
18.250 1.3457 0.13076 0.12722 -0.0884 0.0055 0.7928
18.500 1.3367 0.13733 0.13395 -0.0923 0.0055 0.7980
18.750 1.3272 0.14413 0.14091 -0.0966 0.0055 0.8038
19.000 1.3177 0.15104 0.14798 -0.1011 0.0055 0.8099
19.250 1.3081 0.15806 0.15516 -0.1057 0.0055 0.8171
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Polar data table (+)
Polar graphs
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