EPPLER 403 AIRFOIL (e403-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 403 AIRFOIL (e403-il) Reynolds number: 100,000 Max Cl/Cd: 47.39 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e403-il-100000.txt Download as CSV file: xf-e403-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5231 0.10842 0.10402 -0.0316 1.0000 0.1556
-9.000 -0.5245 0.10589 0.10152 -0.0304 1.0000 0.1616
-7.250 -0.7529 0.05596 0.04986 -0.0448 1.0000 0.0811
-7.000 -0.7343 0.04967 0.04304 -0.0442 1.0000 0.0631
-6.750 -0.7166 0.04500 0.03784 -0.0445 1.0000 0.0585
-6.500 -0.6947 0.04147 0.03361 -0.0448 1.0000 0.0566
-6.250 -0.6722 0.03898 0.03070 -0.0446 1.0000 0.0563
-6.000 -0.6487 0.03706 0.02841 -0.0441 1.0000 0.0554
-5.750 -0.6254 0.03522 0.02627 -0.0434 1.0000 0.0550
-5.500 -0.6032 0.03351 0.02440 -0.0425 1.0000 0.0551
-5.250 -0.5820 0.03191 0.02275 -0.0413 1.0000 0.0558
-5.000 -0.5612 0.03063 0.02149 -0.0402 1.0000 0.0573
-4.750 -0.5400 0.02963 0.02052 -0.0391 1.0000 0.0593
-4.500 -0.5180 0.02884 0.01971 -0.0384 1.0000 0.0632
-4.250 -0.4951 0.02788 0.01882 -0.0381 1.0000 0.0696
-4.000 -0.4694 0.02710 0.01806 -0.0385 1.0000 0.0781
-3.750 -0.4195 0.02382 0.01775 -0.0456 1.0000 0.5470
-3.500 -0.4109 0.02560 0.01947 -0.0400 1.0000 0.5981
-3.250 -0.4054 0.02734 0.02120 -0.0337 1.0000 0.6261
-3.000 -0.4054 0.02933 0.02323 -0.0257 1.0000 0.6543
-2.750 -0.4100 0.03094 0.02491 -0.0165 1.0000 0.6731
-2.500 -0.4079 0.03200 0.02596 -0.0096 1.0000 0.6908
-2.250 -0.4030 0.03274 0.02665 -0.0039 1.0000 0.7078
-2.000 -0.3967 0.03330 0.02715 0.0012 1.0000 0.7254
-1.750 -0.3884 0.03362 0.02740 0.0054 1.0000 0.7409
-1.500 -0.3749 0.03366 0.02735 0.0078 1.0000 0.7516
-1.250 -0.3478 0.03365 0.02716 0.0059 1.0000 0.7609
-1.000 -0.3351 0.03353 0.02697 0.0082 1.0000 0.7664
-0.750 -0.3106 0.03355 0.02687 0.0070 1.0000 0.7729
-0.500 -0.2875 0.03354 0.02675 0.0061 1.0000 0.7779
-0.250 -0.2648 0.03373 0.02685 0.0057 0.9985 0.7824
0.000 -0.1727 0.03595 0.02881 -0.0076 0.9628 0.7876
0.250 -0.1144 0.03651 0.02921 -0.0143 0.9409 0.7919
0.500 -0.0746 0.03679 0.02941 -0.0171 0.9285 0.7954
0.750 -0.0361 0.03693 0.02947 -0.0201 0.9174 0.7995
1.000 0.0010 0.03696 0.02944 -0.0232 0.9054 0.8033
1.250 0.0392 0.03706 0.02949 -0.0264 0.8945 0.8067
1.500 0.0820 0.03727 0.02967 -0.0294 0.8869 0.8102
1.750 0.1106 0.03713 0.02952 -0.0305 0.8749 0.8137
2.000 0.1457 0.03715 0.02953 -0.0330 0.8642 0.8171
2.250 0.1985 0.03730 0.02965 -0.0383 0.8579 0.8209
2.500 0.2231 0.03706 0.02945 -0.0383 0.8458 0.8240
2.750 0.2538 0.03696 0.02938 -0.0395 0.8348 0.8271
3.000 0.3036 0.03678 0.02923 -0.0436 0.8293 0.8310
3.250 0.3367 0.03666 0.02915 -0.0456 0.8172 0.8347
3.500 0.3667 0.03642 0.02898 -0.0464 0.8058 0.8376
3.750 0.4142 0.03580 0.02843 -0.0494 0.8005 0.8410
4.000 0.4441 0.03548 0.02819 -0.0502 0.7880 0.8449
4.250 0.4795 0.03514 0.02794 -0.0519 0.7762 0.8487
4.500 0.5276 0.03417 0.02707 -0.0548 0.7698 0.8519
4.750 0.5606 0.03343 0.02644 -0.0553 0.7584 0.8553
5.000 0.5937 0.03274 0.02589 -0.0560 0.7461 0.8593
5.250 0.6461 0.03128 0.02458 -0.0591 0.7405 0.8635
5.500 0.6816 0.03022 0.02368 -0.0596 0.7289 0.8671
5.750 0.7156 0.02905 0.02265 -0.0597 0.7166 0.8708
6.000 0.7703 0.02682 0.02061 -0.0622 0.7110 0.8751
6.250 0.8186 0.02513 0.01910 -0.0644 0.6972 0.8795
6.500 0.8509 0.02395 0.01806 -0.0638 0.6767 0.8838
6.750 0.9011 0.02236 0.01659 -0.0661 0.6528 0.8880
7.000 0.9470 0.02147 0.01573 -0.0682 0.6182 0.8921
7.250 0.9819 0.02112 0.01531 -0.0687 0.5771 0.8966
7.500 1.0061 0.02123 0.01531 -0.0678 0.5343 0.9018
7.750 1.0269 0.02167 0.01560 -0.0666 0.4900 0.9072
8.000 1.0407 0.02218 0.01593 -0.0643 0.4497 0.9126
8.250 1.0516 0.02287 0.01652 -0.0619 0.4097 0.9186
8.500 1.0605 0.02364 0.01712 -0.0592 0.3715 0.9252
8.750 1.0656 0.02447 0.01787 -0.0561 0.3328 0.9333
9.000 1.0685 0.02538 0.01862 -0.0528 0.2951 0.9422
9.250 1.0709 0.02641 0.01952 -0.0498 0.2549 0.9531
9.500 1.0760 0.02763 0.02060 -0.0476 0.2147 0.9687
9.750 1.0822 0.02918 0.02195 -0.0461 0.1754 1.0000
10.000 1.0876 0.03149 0.02398 -0.0448 0.1299 1.0000
10.250 1.0876 0.03449 0.02659 -0.0429 0.0937 1.0000
10.500 1.0964 0.03705 0.02907 -0.0419 0.0730 1.0000
10.750 1.1112 0.03937 0.03138 -0.0415 0.0631 1.0000
11.000 1.1362 0.04179 0.03360 -0.0420 0.0568 1.0000
11.250 1.1688 0.04387 0.03591 -0.0430 0.0529 1.0000
11.500 1.2019 0.04618 0.03833 -0.0444 0.0496 1.0000
11.750 1.2449 0.04968 0.04184 -0.0471 0.0461 1.0000
12.000 1.2606 0.05245 0.04502 -0.0467 0.0448 1.0000
12.250 1.2754 0.05592 0.04889 -0.0463 0.0441 1.0000
12.500 1.2819 0.05967 0.05304 -0.0453 0.0438 1.0000
12.750 1.2808 0.06364 0.05740 -0.0438 0.0437 1.0000
13.000 1.2738 0.06784 0.06197 -0.0422 0.0438 1.0000
13.250 1.2624 0.07232 0.06680 -0.0408 0.0440 1.0000
13.500 1.2475 0.07709 0.07190 -0.0398 0.0443 1.0000
13.750 1.2299 0.08222 0.07732 -0.0393 0.0446 1.0000
14.000 1.2101 0.08773 0.08310 -0.0395 0.0449 1.0000
14.250 1.1890 0.09369 0.08930 -0.0405 0.0452 1.0000
14.500 1.1675 0.10011 0.09594 -0.0424 0.0456 1.0000
14.750 1.1464 0.10707 0.10309 -0.0453 0.0460 1.0000
15.000 1.1295 0.11444 0.11059 -0.0486 0.0464 1.0000
15.250 1.1046 0.12223 0.11863 -0.0539 0.0470 1.0000
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Polar data table (+)
Polar graphs
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