EPPLER 403 AIRFOIL (e403-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 403 AIRFOIL (e403-il) Reynolds number: 200,000 Max Cl/Cd: 66.81 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e403-il-200000-n5.txt Download as CSV file: xf-e403-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4510 0.08654 0.08267 -0.0892 0.9772 0.0139
-12.000 -0.4828 0.07531 0.07126 -0.0975 0.9753 0.0136
-11.750 -0.5060 0.06750 0.06324 -0.1035 0.9736 0.0134
-11.500 -0.5312 0.06211 0.05766 -0.1052 0.9695 0.0133
-11.250 -0.5504 0.05760 0.05295 -0.1064 0.9656 0.0132
-11.000 -0.5655 0.05315 0.04823 -0.1080 0.9626 0.0131
-10.750 -0.5740 0.04913 0.04392 -0.1097 0.9602 0.0131
-10.500 -0.5910 0.04705 0.04167 -0.1066 0.9544 0.0131
-10.250 -0.6022 0.04450 0.03887 -0.1048 0.9500 0.0130
-10.000 -0.6036 0.04186 0.03593 -0.1044 0.9468 0.0129
-9.750 -0.6086 0.04004 0.03389 -0.1018 0.9421 0.0129
-9.500 -0.6094 0.03840 0.03206 -0.0993 0.9375 0.0131
-9.250 -0.5970 0.03629 0.02966 -0.0988 0.9349 0.0132
-9.000 -0.5786 0.03441 0.02753 -0.0989 0.9331 0.0133
-8.750 -0.5576 0.03277 0.02566 -0.0991 0.9318 0.0135
-8.500 -0.5345 0.03130 0.02400 -0.0994 0.9309 0.0138
-8.250 -0.5405 0.03066 0.02327 -0.0939 0.9243 0.0139
-8.000 -0.5218 0.02962 0.02209 -0.0931 0.9219 0.0144
-7.750 -0.5005 0.02863 0.02096 -0.0927 0.9202 0.0148
-7.500 -0.4761 0.02781 0.01997 -0.0928 0.9187 0.0155
-7.250 -0.4528 0.02663 0.01880 -0.0929 0.9175 0.0160
-7.000 -0.4270 0.02564 0.01778 -0.0936 0.9164 0.0164
-6.750 -0.4281 0.02520 0.01731 -0.0891 0.9102 0.0166
-6.500 -0.4079 0.02439 0.01645 -0.0888 0.9074 0.0171
-6.250 -0.3825 0.02358 0.01558 -0.0894 0.9055 0.0178
-6.000 -0.3547 0.02281 0.01473 -0.0906 0.9040 0.0185
-5.750 -0.3250 0.02213 0.01394 -0.0920 0.9029 0.0194
-5.500 -0.2936 0.02142 0.01316 -0.0938 0.9019 0.0210
-5.250 -0.2787 0.02110 0.01281 -0.0922 0.8973 0.0234
-5.000 -0.2552 0.02067 0.01235 -0.0922 0.8942 0.0268
-4.750 -0.2255 0.02011 0.01179 -0.0935 0.8922 0.0369
-4.500 -0.1915 0.01912 0.01113 -0.0963 0.8908 0.1022
-4.250 -0.1472 0.01691 0.01016 -0.1034 0.8906 0.3627
-4.000 -0.1138 0.01664 0.01053 -0.1050 0.8895 0.5187
-3.750 -0.0820 0.01689 0.01079 -0.1056 0.8881 0.5602
-3.500 -0.0499 0.01728 0.01113 -0.1061 0.8869 0.5872
-3.250 -0.0379 0.01782 0.01168 -0.1028 0.8809 0.5980
-3.000 -0.0113 0.01801 0.01180 -0.1026 0.8779 0.6067
-2.750 0.0184 0.01808 0.01181 -0.1030 0.8757 0.6110
-2.500 0.0515 0.01803 0.01165 -0.1042 0.8742 0.6154
-2.250 0.0871 0.01789 0.01138 -0.1061 0.8729 0.6199
-2.000 0.1207 0.01781 0.01127 -0.1073 0.8718 0.6219
-1.750 0.1331 0.01808 0.01152 -0.1046 0.8644 0.6243
-1.500 0.1635 0.01803 0.01143 -0.1053 0.8617 0.6271
-1.250 0.1974 0.01789 0.01124 -0.1066 0.8598 0.6302
-1.000 0.2339 0.01769 0.01096 -0.1086 0.8584 0.6339
-0.500 0.2827 0.01773 0.01098 -0.1076 0.8483 0.6383
-0.250 0.3162 0.01752 0.01077 -0.1087 0.8458 0.6405
0.000 0.3522 0.01725 0.01049 -0.1103 0.8440 0.6431
0.250 0.3874 0.01697 0.01021 -0.1117 0.8418 0.6459
0.500 0.4052 0.01711 0.01033 -0.1102 0.8329 0.6489
0.750 0.4414 0.01675 0.00996 -0.1118 0.8304 0.6517
1.000 0.4772 0.01636 0.00961 -0.1131 0.8285 0.6535
1.250 0.4930 0.01656 0.00986 -0.1110 0.8189 0.6556
1.500 0.5267 0.01622 0.00955 -0.1120 0.8158 0.6578
1.750 0.5617 0.01587 0.00924 -0.1132 0.8130 0.6603
2.000 0.5802 0.01601 0.00941 -0.1117 0.8030 0.6633
2.250 0.6174 0.01559 0.00900 -0.1134 0.7995 0.6663
2.500 0.6368 0.01567 0.00914 -0.1119 0.7884 0.6683
2.750 0.6657 0.01544 0.00898 -0.1120 0.7801 0.6701
3.250 0.7245 0.01499 0.00866 -0.1123 0.7580 0.6747
3.500 0.7562 0.01476 0.00846 -0.1129 0.7450 0.6774
3.750 0.7928 0.01441 0.00813 -0.1144 0.7294 0.6801
4.000 0.8363 0.01396 0.00766 -0.1171 0.7083 0.6827
4.250 0.8768 0.01368 0.00733 -0.1193 0.6768 0.6844
4.500 0.9122 0.01369 0.00718 -0.1205 0.6334 0.6864
4.750 0.9360 0.01401 0.00731 -0.1197 0.5888 0.6887
5.000 0.9539 0.01447 0.00759 -0.1179 0.5485 0.6913
5.250 0.9697 0.01498 0.00795 -0.1157 0.5110 0.6940
5.500 0.9847 0.01555 0.00836 -0.1136 0.4757 0.6968
5.750 0.9995 0.01612 0.00881 -0.1115 0.4426 0.6992
6.000 1.0133 0.01670 0.00931 -0.1091 0.4109 0.7012
6.250 1.0260 0.01736 0.00985 -0.1067 0.3749 0.7036
6.500 1.0373 0.01814 0.01046 -0.1041 0.3352 0.7063
6.750 1.0490 0.01896 0.01110 -0.1017 0.2925 0.7091
7.000 1.0612 0.01985 0.01177 -0.0996 0.2497 0.7119
7.250 1.0748 0.02074 0.01246 -0.0978 0.2121 0.7145
7.500 1.0884 0.02160 0.01318 -0.0959 0.1778 0.7165
7.750 1.1030 0.02245 0.01393 -0.0942 0.1482 0.7189
8.000 1.1172 0.02338 0.01474 -0.0926 0.1188 0.7217
8.250 1.1316 0.02434 0.01558 -0.0910 0.0930 0.7247
8.500 1.1459 0.02536 0.01648 -0.0895 0.0699 0.7278
8.750 1.1589 0.02649 0.01750 -0.0878 0.0475 0.7304
9.000 1.1707 0.02768 0.01864 -0.0859 0.0322 0.7326
9.250 1.1838 0.02877 0.01976 -0.0842 0.0248 0.7352
9.500 1.1973 0.02985 0.02091 -0.0826 0.0213 0.7381
9.750 1.2106 0.03098 0.02213 -0.0810 0.0193 0.7413
10.000 1.2237 0.03213 0.02339 -0.0795 0.0180 0.7447
10.250 1.2353 0.03336 0.02474 -0.0779 0.0170 0.7474
10.500 1.2446 0.03478 0.02627 -0.0760 0.0161 0.7502
10.750 1.2553 0.03612 0.02776 -0.0744 0.0154 0.7533
11.000 1.2651 0.03756 0.02934 -0.0728 0.0147 0.7566
11.250 1.2741 0.03912 0.03102 -0.0713 0.0141 0.7600
11.500 1.2811 0.04081 0.03284 -0.0696 0.0137 0.7629
11.750 1.2867 0.04267 0.03484 -0.0680 0.0133 0.7662
12.000 1.2908 0.04475 0.03704 -0.0663 0.0130 0.7698
12.250 1.2931 0.04710 0.03951 -0.0648 0.0128 0.7735
12.500 1.2974 0.04932 0.04187 -0.0635 0.0126 0.7769
12.750 1.3017 0.05158 0.04430 -0.0622 0.0124 0.7802
13.000 1.3058 0.05398 0.04687 -0.0611 0.0123 0.7838
13.250 1.3094 0.05653 0.04957 -0.0602 0.0121 0.7877
13.500 1.3127 0.05920 0.05240 -0.0594 0.0119 0.7918
13.750 1.3151 0.06196 0.05535 -0.0586 0.0118 0.7957
14.000 1.3171 0.06490 0.05846 -0.0580 0.0116 0.8003
14.250 1.3186 0.06801 0.06176 -0.0577 0.0115 0.8052
14.500 1.3188 0.07130 0.06526 -0.0574 0.0114 0.8098
14.750 1.3181 0.07481 0.06896 -0.0574 0.0112 0.8149
15.000 1.3163 0.07857 0.07292 -0.0577 0.0111 0.8204
15.250 1.3129 0.08256 0.07710 -0.0582 0.0109 0.8259
15.500 1.3085 0.08683 0.08159 -0.0591 0.0108 0.8322
15.750 1.3031 0.09138 0.08633 -0.0603 0.0106 0.8390
16.000 1.2966 0.09617 0.09133 -0.0617 0.0105 0.8472
16.250 1.2893 0.10116 0.09652 -0.0635 0.0104 0.8570
16.500 1.2806 0.10643 0.10199 -0.0656 0.0103 0.8698
16.750 1.2701 0.11183 0.10761 -0.0676 0.0102 0.8902
17.000 1.2568 0.11689 0.11288 -0.0694 0.0102 1.0000
17.250 1.2470 0.12343 0.11959 -0.0733 0.0101 1.0000
17.500 1.2363 0.13040 0.12675 -0.0777 0.0101 1.0000
17.750 1.2245 0.13784 0.13437 -0.0826 0.0101 1.0000
18.000 1.2091 0.14646 0.14321 -0.0884 0.0101 1.0000
18.250 1.1924 0.15584 0.15280 -0.0950 0.0101 1.0000
18.500 1.1656 0.16882 0.16606 -0.1042 0.0103 1.0000
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Polar data table (+)
Polar graphs
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