EPPLER 403 AIRFOIL (e403-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 403 AIRFOIL (e403-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.34 at α=1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e403-il-1000000-n5.txt Download as CSV file: xf-e403-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.5715 0.07511 0.07267 -0.1153 0.9786 0.0048
-15.250 -0.5735 0.06976 0.06724 -0.1196 0.9774 0.0049
-15.000 -0.5959 0.06119 0.05845 -0.1259 0.9762 0.0049
-14.750 -0.6016 0.05569 0.05279 -0.1306 0.9752 0.0049
-14.500 -0.6029 0.05103 0.04798 -0.1348 0.9743 0.0049
-14.250 -0.6105 0.04553 0.04225 -0.1394 0.9734 0.0049
-14.000 -0.6106 0.04229 0.03888 -0.1414 0.9703 0.0049
-13.750 -0.6075 0.03946 0.03591 -0.1432 0.9671 0.0050
-13.500 -0.6012 0.03678 0.03308 -0.1453 0.9647 0.0050
-13.250 -0.5932 0.03420 0.03034 -0.1474 0.9624 0.0050
-13.000 -0.5802 0.03216 0.02817 -0.1495 0.9604 0.0051
-12.750 -0.5692 0.03063 0.02653 -0.1502 0.9573 0.0052
-12.500 -0.5598 0.02922 0.02502 -0.1502 0.9531 0.0052
-12.250 -0.5493 0.02755 0.02322 -0.1505 0.9495 0.0054
-12.000 -0.5346 0.02622 0.02178 -0.1511 0.9468 0.0054
-11.750 -0.5226 0.02500 0.02045 -0.1509 0.9438 0.0054
-11.500 -0.5138 0.02384 0.01919 -0.1498 0.9402 0.0056
-11.250 -0.5009 0.02287 0.01814 -0.1492 0.9368 0.0057
-11.000 -0.4875 0.02182 0.01699 -0.1487 0.9338 0.0057
-10.750 -0.4715 0.02094 0.01602 -0.1484 0.9313 0.0059
-10.500 -0.4583 0.02021 0.01523 -0.1474 0.9287 0.0060
-10.250 -0.4475 0.01935 0.01431 -0.1460 0.9257 0.0060
-10.000 -0.4356 0.01855 0.01345 -0.1448 0.9226 0.0060
-9.750 -0.4204 0.01787 0.01271 -0.1439 0.9200 0.0061
-9.500 -0.4008 0.01744 0.01221 -0.1436 0.9180 0.0063
-9.250 -0.3887 0.01664 0.01136 -0.1423 0.9154 0.0063
-9.000 -0.3794 0.01601 0.01069 -0.1402 0.9125 0.0063
-8.750 -0.3762 0.01515 0.00977 -0.1375 0.9088 0.0065
-8.500 -0.3617 0.01442 0.00900 -0.1367 0.9063 0.0067
-8.250 -0.3422 0.01380 0.00834 -0.1367 0.9043 0.0069
-8.000 -0.3198 0.01329 0.00778 -0.1369 0.9024 0.0070
-7.750 -0.2973 0.01283 0.00728 -0.1370 0.9006 0.0072
-7.500 -0.2754 0.01242 0.00685 -0.1367 0.8990 0.0074
-7.250 -0.2523 0.01203 0.00644 -0.1366 0.8972 0.0076
-7.000 -0.2281 0.01166 0.00603 -0.1367 0.8954 0.0079
-6.750 -0.2029 0.01130 0.00565 -0.1369 0.8936 0.0081
-6.500 -0.1767 0.01100 0.00531 -0.1372 0.8921 0.0085
-6.250 -0.1497 0.01073 0.00503 -0.1376 0.8906 0.0088
-6.000 -0.1226 0.01036 0.00462 -0.1382 0.8892 0.0094
-5.750 -0.0944 0.01007 0.00430 -0.1388 0.8878 0.0099
-5.500 -0.0655 0.00983 0.00404 -0.1396 0.8865 0.0105
-5.250 -0.0382 0.00963 0.00382 -0.1399 0.8850 0.0113
-5.000 -0.0109 0.00944 0.00362 -0.1402 0.8834 0.0120
-4.750 0.0169 0.00922 0.00341 -0.1407 0.8817 0.0145
-4.500 0.0452 0.00882 0.00314 -0.1414 0.8799 0.0448
-4.250 0.0743 0.00827 0.00284 -0.1426 0.8782 0.1094
-4.000 0.1045 0.00769 0.00254 -0.1441 0.8766 0.1899
-3.750 0.1360 0.00698 0.00220 -0.1460 0.8751 0.2982
-3.500 0.1698 0.00610 0.00184 -0.1486 0.8737 0.4526
-3.250 0.2013 0.00589 0.00177 -0.1498 0.8721 0.5070
-3.000 0.2308 0.00582 0.00177 -0.1503 0.8700 0.5358
-2.750 0.2592 0.00579 0.00177 -0.1506 0.8669 0.5493
-2.500 0.2880 0.00577 0.00172 -0.1509 0.8631 0.5570
-2.250 0.3177 0.00572 0.00166 -0.1514 0.8591 0.5622
-2.000 0.3467 0.00570 0.00162 -0.1517 0.8548 0.5663
-1.750 0.3746 0.00568 0.00159 -0.1518 0.8494 0.5693
-1.500 0.4038 0.00567 0.00153 -0.1522 0.8446 0.5719
-1.250 0.4327 0.00565 0.00150 -0.1525 0.8401 0.5742
-1.000 0.4609 0.00564 0.00150 -0.1528 0.8351 0.5766
-0.750 0.4898 0.00564 0.00148 -0.1531 0.8301 0.5791
-0.500 0.5183 0.00564 0.00148 -0.1533 0.8249 0.5815
-0.250 0.5465 0.00565 0.00148 -0.1535 0.8184 0.5840
0.000 0.5748 0.00567 0.00147 -0.1537 0.8115 0.5863
0.250 0.6024 0.00570 0.00147 -0.1537 0.8015 0.5882
0.500 0.6292 0.00573 0.00148 -0.1536 0.7879 0.5903
0.750 0.6550 0.00581 0.00150 -0.1532 0.7708 0.5925
1.000 0.6799 0.00592 0.00154 -0.1527 0.7510 0.5947
1.250 0.7024 0.00609 0.00161 -0.1516 0.7247 0.5968
1.500 0.7225 0.00633 0.00172 -0.1500 0.6929 0.5990
1.750 0.7399 0.00665 0.00187 -0.1479 0.6543 0.6012
2.000 0.7560 0.00701 0.00204 -0.1456 0.6164 0.6031
2.250 0.7725 0.00735 0.00223 -0.1434 0.5785 0.6050
2.500 0.7867 0.00771 0.00243 -0.1407 0.5396 0.6069
2.750 0.8011 0.00809 0.00266 -0.1381 0.4999 0.6089
3.000 0.8180 0.00846 0.00288 -0.1361 0.4643 0.6111
3.250 0.8369 0.00880 0.00310 -0.1345 0.4340 0.6132
3.500 0.8568 0.00914 0.00333 -0.1331 0.4064 0.6152
3.750 0.8765 0.00951 0.00357 -0.1317 0.3763 0.6170
4.000 0.8950 0.00995 0.00384 -0.1301 0.3388 0.6188
4.250 0.9134 0.01041 0.00413 -0.1286 0.3022 0.6207
4.500 0.9313 0.01093 0.00447 -0.1269 0.2594 0.6227
4.750 0.9501 0.01142 0.00480 -0.1255 0.2246 0.6247
5.000 0.9690 0.01193 0.00515 -0.1241 0.1895 0.6266
5.250 0.9877 0.01246 0.00551 -0.1227 0.1563 0.6285
5.500 1.0073 0.01293 0.00587 -0.1215 0.1307 0.6304
5.750 1.0266 0.01344 0.00625 -0.1202 0.1061 0.6323
6.000 1.0463 0.01393 0.00663 -0.1190 0.0855 0.6341
6.250 1.0662 0.01441 0.00703 -0.1178 0.0668 0.6359
6.500 1.0846 0.01499 0.00751 -0.1165 0.0459 0.6379
6.750 1.1030 0.01558 0.00802 -0.1151 0.0296 0.6398
7.000 1.1203 0.01626 0.00860 -0.1135 0.0128 0.6416
7.250 1.1406 0.01672 0.00907 -0.1125 0.0101 0.6436
7.500 1.1613 0.01713 0.00951 -0.1115 0.0091 0.6455
7.750 1.1816 0.01757 0.00997 -0.1104 0.0085 0.6475
8.000 1.2013 0.01804 0.01047 -0.1093 0.0080 0.6495
8.250 1.2207 0.01854 0.01100 -0.1082 0.0076 0.6512
8.500 1.2397 0.01909 0.01160 -0.1070 0.0072 0.6533
8.750 1.2590 0.01959 0.01215 -0.1058 0.0070 0.6553
9.000 1.2777 0.02012 0.01274 -0.1047 0.0068 0.6572
9.250 1.2961 0.02069 0.01336 -0.1034 0.0067 0.6592
9.500 1.3142 0.02128 0.01400 -0.1022 0.0065 0.6613
9.750 1.3315 0.02193 0.01470 -0.1009 0.0063 0.6634
10.000 1.3483 0.02260 0.01543 -0.0995 0.0061 0.6655
10.250 1.3647 0.02332 0.01619 -0.0981 0.0060 0.6673
10.500 1.3809 0.02404 0.01698 -0.0967 0.0058 0.6695
10.750 1.3959 0.02486 0.01785 -0.0952 0.0057 0.6715
11.000 1.4102 0.02574 0.01880 -0.0936 0.0055 0.6736
11.250 1.4226 0.02677 0.01990 -0.0919 0.0053 0.6757
11.500 1.4326 0.02800 0.02121 -0.0898 0.0051 0.6778
11.750 1.4440 0.02912 0.02242 -0.0880 0.0051 0.6801
12.000 1.4562 0.03017 0.02353 -0.0864 0.0050 0.6822
12.250 1.4682 0.03126 0.02471 -0.0849 0.0050 0.6844
12.500 1.4787 0.03248 0.02601 -0.0832 0.0049 0.6868
12.750 1.4888 0.03376 0.02739 -0.0816 0.0048 0.6891
13.000 1.4977 0.03514 0.02887 -0.0799 0.0048 0.6914
13.250 1.5061 0.03662 0.03043 -0.0783 0.0047 0.6937
13.500 1.5133 0.03823 0.03213 -0.0767 0.0047 0.6960
13.750 1.5197 0.03995 0.03395 -0.0751 0.0046 0.6983
14.000 1.5252 0.04180 0.03590 -0.0736 0.0045 0.7008
14.250 1.5301 0.04379 0.03800 -0.0722 0.0045 0.7035
14.500 1.5339 0.04595 0.04026 -0.0709 0.0044 0.7062
14.750 1.5370 0.04825 0.04267 -0.0697 0.0044 0.7089
15.000 1.5391 0.05075 0.04528 -0.0687 0.0043 0.7114
15.250 1.5404 0.05341 0.04805 -0.0678 0.0043 0.7137
15.500 1.5405 0.05633 0.05109 -0.0671 0.0042 0.7162
15.750 1.5399 0.05947 0.05435 -0.0667 0.0042 0.7189
16.000 1.5383 0.06286 0.05787 -0.0665 0.0041 0.7219
16.250 1.5358 0.06651 0.06164 -0.0666 0.0041 0.7250
16.500 1.5318 0.07050 0.06575 -0.0669 0.0041 0.7279
17.000 1.5214 0.07939 0.07491 -0.0687 0.0040 0.7338
17.250 1.5141 0.08443 0.08008 -0.0701 0.0040 0.7369
17.500 1.5060 0.08978 0.08557 -0.0719 0.0040 0.7399
17.750 1.4967 0.09549 0.09142 -0.0741 0.0039 0.7426
18.000 1.4857 0.10167 0.09774 -0.0767 0.0039 0.7451
18.250 1.4752 0.10794 0.10415 -0.0797 0.0039 0.7478
18.500 1.4634 0.11462 0.11098 -0.0830 0.0039 0.7506
18.750 1.4506 0.12159 0.11808 -0.0867 0.0039 0.7534
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