EPPLER 403 AIRFOIL (e403-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: EPPLER 403 AIRFOIL (e403-il) Reynolds number: 50,000 Max Cl/Cd: 33.3 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e403-il-50000.txt Download as CSV file: xf-e403-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5810 0.10213 0.09596 -0.0402 1.0000 0.1665
-8.750 -0.5957 0.09304 0.08692 -0.0427 1.0000 0.1402
-8.500 -0.6518 0.08828 0.08224 -0.0426 1.0000 0.1389
-8.250 -0.7033 0.08357 0.07739 -0.0438 1.0000 0.1361
-8.000 -0.7007 0.07812 0.07194 -0.0431 1.0000 0.1271
-7.750 -0.7297 0.07224 0.06564 -0.0443 1.0000 0.1198
-7.500 -0.7300 0.06743 0.06066 -0.0441 1.0000 0.1149
-7.250 -0.7368 0.06163 0.05390 -0.0458 1.0000 0.1066
-7.000 -0.7240 0.05746 0.04956 -0.0455 1.0000 0.1039
-6.750 -0.7099 0.05331 0.04499 -0.0458 1.0000 0.1010
-6.500 -0.6917 0.04956 0.04072 -0.0462 1.0000 0.0990
-6.250 -0.6711 0.04653 0.03725 -0.0462 1.0000 0.0995
-6.000 -0.6490 0.04398 0.03429 -0.0460 1.0000 0.1009
-5.750 -0.6258 0.04164 0.03156 -0.0455 1.0000 0.1031
-5.500 -0.6027 0.03968 0.02928 -0.0443 1.0000 0.1047
-5.250 -0.5801 0.03814 0.02743 -0.0427 1.0000 0.1071
-5.000 -0.5623 0.03673 0.02620 -0.0396 1.0000 0.1116
-4.750 -0.5436 0.03585 0.02523 -0.0369 1.0000 0.1207
-4.500 -0.5275 0.03485 0.02441 -0.0338 1.0000 0.1330
-4.250 -0.5101 0.03347 0.02325 -0.0317 1.0000 0.1546
-4.000 -0.4986 0.02988 0.02301 -0.0295 1.0000 0.4492
-3.750 -0.5120 0.03592 0.02898 -0.0119 1.0000 0.6313
-3.500 -0.5225 0.03915 0.03217 0.0024 1.0000 0.6762
-3.250 -0.5286 0.04131 0.03425 0.0148 1.0000 0.7181
-3.000 -0.5295 0.04266 0.03545 0.0254 1.0000 0.7591
-2.750 -0.5193 0.04362 0.03621 0.0344 1.0000 0.8036
-2.500 -0.4802 0.04411 0.03634 0.0366 1.0000 0.8472
-2.250 -0.4325 0.04382 0.03564 0.0336 1.0000 0.8738
-2.000 -0.4062 0.04311 0.03468 0.0325 1.0000 0.8887
-1.750 -0.3828 0.04239 0.03374 0.0316 1.0000 0.9000
-1.500 -0.3814 0.04151 0.03275 0.0344 1.0000 0.9090
-1.250 -0.3518 0.04097 0.03198 0.0322 1.0000 0.9175
-1.000 -0.3417 0.04026 0.03115 0.0332 1.0000 0.9245
-0.750 -0.3217 0.03975 0.03050 0.0325 1.0000 0.9312
-0.500 -0.3131 0.03914 0.02978 0.0338 1.0000 0.9371
-0.250 -0.2878 0.03883 0.02932 0.0321 1.0000 0.9427
0.000 -0.2840 0.03826 0.02868 0.0341 1.0000 0.9482
0.250 -0.2513 0.03821 0.02851 0.0309 1.0000 0.9531
0.500 -0.2322 0.03802 0.02824 0.0301 1.0000 0.9583
0.750 -0.2100 0.03796 0.02808 0.0287 1.0000 0.9632
1.000 -0.1810 0.03810 0.02815 0.0259 1.0000 0.9680
1.250 -0.1606 0.03818 0.02818 0.0247 1.0000 0.9732
1.500 -0.1280 0.03854 0.02847 0.0211 1.0000 0.9778
1.750 -0.1021 0.03886 0.02877 0.0187 1.0000 0.9831
2.000 -0.0747 0.03925 0.02915 0.0158 1.0000 0.9880
2.250 -0.0504 0.03966 0.02956 0.0135 1.0000 0.9936
2.500 -0.0301 0.04011 0.03002 0.0118 1.0000 1.0000
2.750 -0.0305 0.03994 0.02987 0.0138 1.0000 1.0000
3.000 -0.0306 0.03977 0.02973 0.0157 1.0000 1.0000
3.250 -0.0300 0.03964 0.02963 0.0175 1.0000 1.0000
3.500 -0.0259 0.03968 0.02971 0.0184 1.0000 1.0000
3.750 -0.0164 0.04006 0.03012 0.0183 1.0000 1.0000
4.000 -0.0003 0.04085 0.03095 0.0169 0.9991 1.0000
4.250 0.1405 0.04639 0.03649 -0.0048 0.9122 1.0000
4.500 0.1895 0.04756 0.03770 -0.0102 0.8849 1.0000
4.750 0.2260 0.04826 0.03847 -0.0137 0.8618 1.0000
5.000 0.2689 0.04916 0.03946 -0.0180 0.8407 1.0000
5.250 0.3055 0.04985 0.04024 -0.0212 0.8199 1.0000
5.500 0.3551 0.05064 0.04118 -0.0261 0.8011 1.0000
5.750 0.3877 0.05123 0.04189 -0.0286 0.7803 1.0000
6.000 0.4314 0.05175 0.04255 -0.0323 0.7605 1.0000
6.250 0.4843 0.05193 0.04294 -0.0367 0.7423 1.0000
6.500 0.5148 0.05243 0.04360 -0.0385 0.7205 1.0000
6.750 0.5610 0.05237 0.04374 -0.0415 0.7007 1.0000
7.000 0.6179 0.05153 0.04317 -0.0450 0.6824 1.0000
7.250 0.6487 0.05176 0.04361 -0.0461 0.6590 1.0000
7.500 0.7078 0.04998 0.04216 -0.0487 0.6391 1.0000
7.750 0.7867 0.04574 0.03832 -0.0511 0.6214 1.0000
8.000 0.8421 0.04286 0.03580 -0.0518 0.5965 1.0000
8.250 0.9857 0.03361 0.02703 -0.0582 0.5581 1.0000
8.500 1.0403 0.03223 0.02564 -0.0596 0.5025 1.0000
8.750 1.0763 0.03232 0.02551 -0.0595 0.4449 1.0000
9.000 1.0981 0.03316 0.02609 -0.0581 0.3909 1.0000
9.250 1.1121 0.03449 0.02712 -0.0561 0.3407 1.0000
9.500 1.1198 0.03614 0.02851 -0.0535 0.2938 1.0000
9.750 1.1238 0.03800 0.03005 -0.0507 0.2493 1.0000
10.000 1.1217 0.04005 0.03192 -0.0476 0.2109 1.0000
10.250 1.1242 0.04244 0.03397 -0.0453 0.1741 1.0000
10.500 1.1359 0.04533 0.03675 -0.0440 0.1421 1.0000
10.750 1.1679 0.04875 0.03997 -0.0450 0.1177 1.0000
11.000 1.2032 0.05261 0.04398 -0.0465 0.1044 1.0000
11.250 1.2247 0.05650 0.04832 -0.0463 0.0982 1.0000
11.500 1.2532 0.06102 0.05293 -0.0477 0.0925 1.0000
11.750 1.2455 0.06452 0.05697 -0.0446 0.0909 1.0000
12.000 1.2360 0.06837 0.06126 -0.0419 0.0896 1.0000
12.250 1.2228 0.07247 0.06576 -0.0394 0.0890 1.0000
12.500 1.2055 0.07689 0.07053 -0.0372 0.0888 1.0000
12.750 1.1843 0.08171 0.07568 -0.0356 0.0890 1.0000
13.000 1.1601 0.08702 0.08128 -0.0348 0.0895 1.0000
13.250 1.1342 0.09289 0.08741 -0.0349 0.0902 1.0000
13.500 1.1081 0.09938 0.09410 -0.0363 0.0911 1.0000
13.750 1.0833 0.10648 0.10136 -0.0387 0.0920 1.0000
14.000 1.0626 0.11400 0.10899 -0.0419 0.0928 1.0000
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Polar data table (+)
Polar graphs
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