EPPLER 426 AIRFOIL (e426-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 426 AIRFOIL (e426-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.35 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e426-il-1000000.txt Download as CSV file: xf-e426-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 426 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -1.1126 0.08372 0.08055 -0.0141 1.0000 0.0119
-16.000 -1.1517 0.07373 0.07044 -0.0199 1.0000 0.0118
-15.750 -1.1948 0.06279 0.05934 -0.0264 1.0000 0.0116
-15.500 -1.2346 0.05207 0.04841 -0.0334 1.0000 0.0116
-15.250 -1.2621 0.04365 0.03979 -0.0396 1.0000 0.0115
-15.000 -1.2782 0.03771 0.03369 -0.0439 1.0000 0.0115
-14.750 -1.2863 0.03372 0.02957 -0.0462 1.0000 0.0117
-14.500 -1.2915 0.03083 0.02655 -0.0470 1.0000 0.0118
-14.250 -1.2963 0.02868 0.02429 -0.0462 1.0000 0.0118
-14.000 -1.2989 0.02718 0.02269 -0.0438 1.0000 0.0120
-13.750 -1.2947 0.02596 0.02137 -0.0417 1.0000 0.0121
-13.500 -1.2829 0.02491 0.02023 -0.0403 1.0000 0.0122
-13.250 -1.2688 0.02396 0.01919 -0.0391 1.0000 0.0124
-13.000 -1.2603 0.02239 0.01751 -0.0375 1.0000 0.0127
-12.750 -1.2456 0.02126 0.01630 -0.0364 1.0000 0.0131
-12.500 -1.2277 0.02038 0.01536 -0.0354 1.0000 0.0134
-12.250 -1.2080 0.01963 0.01454 -0.0345 1.0000 0.0138
-12.000 -1.1875 0.01893 0.01378 -0.0337 1.0000 0.0142
-11.750 -1.1663 0.01828 0.01306 -0.0329 1.0000 0.0147
-11.500 -1.1441 0.01770 0.01241 -0.0322 1.0000 0.0151
-11.250 -1.1241 0.01679 0.01145 -0.0313 1.0000 0.0159
-11.000 -1.1020 0.01616 0.01077 -0.0306 1.0000 0.0167
-10.750 -1.0789 0.01563 0.01019 -0.0299 1.0000 0.0176
-10.500 -1.0560 0.01504 0.00956 -0.0291 1.0000 0.0189
-10.250 -1.0331 0.01445 0.00895 -0.0284 1.0000 0.0205
-10.000 -1.0096 0.01393 0.00840 -0.0277 1.0000 0.0226
-9.750 -0.9862 0.01339 0.00785 -0.0270 1.0000 0.0252
-9.500 -0.9629 0.01284 0.00729 -0.0263 1.0000 0.0286
-9.250 -0.9393 0.01232 0.00678 -0.0255 1.0000 0.0327
-9.000 -0.9159 0.01179 0.00625 -0.0248 1.0000 0.0383
-8.750 -0.8931 0.01118 0.00574 -0.0240 1.0000 0.0501
-8.500 -0.8686 0.01082 0.00547 -0.0233 1.0000 0.0633
-8.250 -0.8435 0.01055 0.00524 -0.0227 1.0000 0.0695
-8.000 -0.8176 0.01042 0.00508 -0.0221 1.0000 0.0732
-7.750 -0.7925 0.01016 0.00482 -0.0215 1.0000 0.0769
-7.500 -0.7673 0.00993 0.00461 -0.0208 1.0000 0.0802
-7.250 -0.7418 0.00975 0.00441 -0.0202 1.0000 0.0827
-7.000 -0.7162 0.00961 0.00424 -0.0196 1.0000 0.0843
-6.750 -0.6911 0.00938 0.00400 -0.0189 1.0000 0.0868
-6.500 -0.6661 0.00913 0.00378 -0.0182 1.0000 0.0904
-6.250 -0.6409 0.00895 0.00361 -0.0175 1.0000 0.0938
-6.000 -0.6155 0.00883 0.00347 -0.0168 1.0000 0.0962
-5.750 -0.5907 0.00860 0.00326 -0.0161 1.0000 0.0996
-5.500 -0.5658 0.00841 0.00310 -0.0153 1.0000 0.1032
-5.250 -0.5314 0.00825 0.00296 -0.0165 0.9982 0.1072
-5.000 -0.4930 0.00806 0.00280 -0.0186 0.9948 0.1129
-4.750 -0.4560 0.00789 0.00267 -0.0204 0.9905 0.1198
-4.500 -0.4173 0.00770 0.00253 -0.0226 0.9848 0.1280
-4.250 -0.3771 0.00756 0.00240 -0.0249 0.9713 0.1352
-4.000 -0.3322 0.00736 0.00222 -0.0282 0.9273 0.1445
-3.750 -0.3029 0.00741 0.00210 -0.0281 0.8792 0.1495
-3.500 -0.2767 0.00741 0.00199 -0.0274 0.8436 0.1544
-3.250 -0.2505 0.00740 0.00189 -0.0267 0.8073 0.1601
-3.000 -0.2239 0.00743 0.00180 -0.0261 0.7726 0.1645
-2.750 -0.1968 0.00746 0.00171 -0.0257 0.7445 0.1683
-2.500 -0.1694 0.00741 0.00162 -0.0253 0.7215 0.1748
-2.250 -0.1419 0.00739 0.00155 -0.0250 0.6987 0.1801
-2.000 -0.1143 0.00740 0.00147 -0.0247 0.6754 0.1855
-1.750 -0.0867 0.00736 0.00140 -0.0244 0.6512 0.1937
-1.500 -0.0590 0.00735 0.00134 -0.0241 0.6280 0.2018
-1.250 -0.0313 0.00731 0.00128 -0.0239 0.6058 0.2142
-1.000 -0.0037 0.00726 0.00123 -0.0236 0.5831 0.2324
-0.750 0.0236 0.00716 0.00118 -0.0234 0.5603 0.2651
-0.500 0.0506 0.00697 0.00113 -0.0231 0.5378 0.3225
-0.250 0.0776 0.00681 0.00110 -0.0229 0.5142 0.3859
0.000 0.1047 0.00672 0.00110 -0.0226 0.4897 0.4395
0.250 0.1321 0.00668 0.00112 -0.0223 0.4632 0.4832
0.500 0.1594 0.00671 0.00114 -0.0220 0.4323 0.5160
0.750 0.1865 0.00679 0.00117 -0.0217 0.3944 0.5454
1.000 0.2132 0.00695 0.00123 -0.0214 0.3436 0.5754
1.250 0.2395 0.00714 0.00132 -0.0210 0.2927 0.6089
1.500 0.2665 0.00725 0.00141 -0.0207 0.2647 0.6423
2.000 0.3213 0.00739 0.00158 -0.0201 0.2347 0.6959
2.500 0.3760 0.00750 0.00176 -0.0194 0.2155 0.7490
2.750 0.4030 0.00753 0.00187 -0.0190 0.2085 0.7797
3.000 0.4295 0.00751 0.00197 -0.0184 0.2031 0.8190
3.250 0.4544 0.00750 0.00208 -0.0174 0.1971 0.8676
3.500 0.4784 0.00744 0.00220 -0.0161 0.1923 0.9310
3.750 0.5182 0.00751 0.00229 -0.0183 0.1872 0.9824
4.000 0.5575 0.00766 0.00240 -0.0206 0.1814 1.0000
4.250 0.5839 0.00782 0.00253 -0.0201 0.1768 1.0000
4.500 0.6109 0.00792 0.00263 -0.0198 0.1735 1.0000
4.750 0.6377 0.00805 0.00274 -0.0194 0.1692 1.0000
5.000 0.6644 0.00824 0.00289 -0.0189 0.1638 1.0000
5.250 0.6915 0.00837 0.00302 -0.0186 0.1600 1.0000
5.500 0.7187 0.00849 0.00314 -0.0183 0.1552 1.0000
5.750 0.7454 0.00871 0.00329 -0.0179 0.1473 1.0000
6.000 0.7728 0.00882 0.00341 -0.0176 0.1424 1.0000
6.250 0.7996 0.00902 0.00356 -0.0173 0.1348 1.0000
6.500 0.8266 0.00919 0.00373 -0.0170 0.1287 1.0000
6.750 0.8531 0.00943 0.00391 -0.0166 0.1206 1.0000
7.000 0.8798 0.00964 0.00410 -0.0163 0.1144 1.0000
7.250 0.9060 0.00992 0.00433 -0.0159 0.1065 1.0000
7.500 0.9325 0.01015 0.00455 -0.0155 0.1016 1.0000
7.750 0.9585 0.01046 0.00483 -0.0151 0.0958 1.0000
8.000 0.9850 0.01068 0.00507 -0.0148 0.0924 1.0000
8.250 1.0111 0.01095 0.00533 -0.0144 0.0880 1.0000
8.500 1.0368 0.01127 0.00563 -0.0139 0.0830 1.0000
8.750 1.0630 0.01151 0.00589 -0.0136 0.0791 1.0000
9.000 1.0882 0.01189 0.00622 -0.0131 0.0728 1.0000
9.250 1.1140 0.01216 0.00650 -0.0127 0.0683 1.0000
9.500 1.1389 0.01255 0.00686 -0.0122 0.0625 1.0000
9.750 1.1637 0.01293 0.00722 -0.0117 0.0570 1.0000
10.000 1.1884 0.01333 0.00761 -0.0112 0.0523 1.0000
10.250 1.2122 0.01381 0.00806 -0.0106 0.0470 1.0000
10.500 1.2360 0.01427 0.00851 -0.0100 0.0422 1.0000
10.750 1.2597 0.01474 0.00897 -0.0094 0.0383 1.0000
11.000 1.2825 0.01529 0.00951 -0.0087 0.0338 1.0000
11.250 1.3046 0.01590 0.01010 -0.0079 0.0284 1.0000
11.500 1.3247 0.01670 0.01085 -0.0070 0.0202 1.0000
11.750 1.3420 0.01778 0.01188 -0.0057 0.0121 1.0000
12.000 1.3614 0.01858 0.01270 -0.0047 0.0107 1.0000
12.250 1.3806 0.01935 0.01353 -0.0036 0.0098 1.0000
12.500 1.3997 0.02006 0.01432 -0.0026 0.0094 1.0000
12.750 1.4179 0.02082 0.01514 -0.0014 0.0091 1.0000
13.000 1.4338 0.02172 0.01611 0.0000 0.0087 1.0000
13.250 1.4478 0.02270 0.01717 0.0015 0.0084 1.0000
13.500 1.4594 0.02375 0.01830 0.0033 0.0082 1.0000
14.000 1.4689 0.02599 0.02073 0.0086 0.0079 1.0000
14.250 1.4719 0.02716 0.02199 0.0111 0.0078 1.0000
14.500 1.4726 0.02861 0.02354 0.0132 0.0078 1.0000
14.750 1.4706 0.03047 0.02551 0.0147 0.0077 1.0000
15.000 1.4666 0.03282 0.02797 0.0155 0.0076 1.0000
15.250 1.4614 0.03567 0.03094 0.0154 0.0076 1.0000
15.500 1.4535 0.03924 0.03464 0.0145 0.0075 1.0000
15.750 1.4417 0.04375 0.03929 0.0126 0.0075 1.0000
16.000 1.4257 0.04933 0.04502 0.0097 0.0075 1.0000
16.250 1.4042 0.05619 0.05205 0.0058 0.0075 1.0000
16.500 1.3711 0.06540 0.06144 0.0004 0.0075 1.0000
16.750 1.3338 0.07578 0.07203 -0.0056 0.0077 1.0000
17.000 1.2868 0.08812 0.08456 -0.0127 0.0078 1.0000
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Polar data table (+)
Polar graphs
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