EPPLER 426 AIRFOIL (e426-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 426 AIRFOIL (e426-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.05 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e426-il-1000000-n5.txt Download as CSV file: xf-e426-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -1.1666 0.07929 0.07599 -0.0175 1.0000 0.0086
-16.250 -1.2606 0.05943 0.05578 -0.0297 1.0000 0.0083
-16.000 -1.3059 0.04777 0.04385 -0.0379 1.0000 0.0082
-15.750 -1.3274 0.04077 0.03667 -0.0430 1.0000 0.0082
-15.500 -1.3435 0.03549 0.03122 -0.0464 1.0000 0.0083
-15.250 -1.3516 0.03204 0.02765 -0.0478 1.0000 0.0083
-15.000 -1.3568 0.02959 0.02508 -0.0477 1.0000 0.0084
-14.750 -1.3601 0.02782 0.02321 -0.0461 1.0000 0.0085
-14.500 -1.3601 0.02654 0.02185 -0.0436 1.0000 0.0086
-14.250 -1.3524 0.02542 0.02064 -0.0418 1.0000 0.0087
-14.000 -1.3404 0.02437 0.01952 -0.0404 1.0000 0.0089
-13.750 -1.3262 0.02342 0.01849 -0.0392 1.0000 0.0090
-13.500 -1.3100 0.02255 0.01755 -0.0382 1.0000 0.0092
-13.250 -1.2925 0.02173 0.01665 -0.0372 1.0000 0.0094
-13.000 -1.2740 0.02097 0.01582 -0.0363 1.0000 0.0096
-12.750 -1.2543 0.02026 0.01505 -0.0354 1.0000 0.0098
-12.500 -1.2339 0.01960 0.01432 -0.0346 1.0000 0.0099
-12.250 -1.2139 0.01884 0.01351 -0.0338 1.0000 0.0102
-12.000 -1.1929 0.01816 0.01277 -0.0330 1.0000 0.0106
-11.750 -1.1711 0.01755 0.01211 -0.0323 1.0000 0.0110
-11.500 -1.1488 0.01697 0.01149 -0.0316 1.0000 0.0114
-11.250 -1.1259 0.01645 0.01092 -0.0309 1.0000 0.0119
-11.000 -1.1026 0.01596 0.01039 -0.0303 1.0000 0.0124
-10.750 -1.0797 0.01541 0.00981 -0.0296 1.0000 0.0132
-10.500 -1.0563 0.01492 0.00929 -0.0289 1.0000 0.0142
-10.250 -1.0323 0.01449 0.00883 -0.0283 1.0000 0.0150
-10.000 -1.0087 0.01400 0.00833 -0.0276 1.0000 0.0164
-9.750 -0.9846 0.01359 0.00789 -0.0270 1.0000 0.0178
-9.500 -0.9605 0.01316 0.00745 -0.0263 1.0000 0.0196
-9.250 -0.9362 0.01277 0.00705 -0.0257 1.0000 0.0215
-9.000 -0.9121 0.01236 0.00663 -0.0250 1.0000 0.0239
-8.750 -0.8877 0.01199 0.00625 -0.0243 1.0000 0.0265
-8.500 -0.8634 0.01160 0.00587 -0.0236 1.0000 0.0298
-8.250 -0.8392 0.01121 0.00548 -0.0229 1.0000 0.0338
-8.000 -0.8151 0.01077 0.00508 -0.0222 1.0000 0.0406
-7.750 -0.7915 0.01028 0.00471 -0.0214 1.0000 0.0551
-7.500 -0.7665 0.01002 0.00448 -0.0208 1.0000 0.0629
-7.250 -0.7413 0.00978 0.00426 -0.0201 1.0000 0.0667
-7.000 -0.7144 0.00957 0.00406 -0.0198 0.9996 0.0704
-6.750 -0.6800 0.00940 0.00388 -0.0211 0.9965 0.0729
-6.500 -0.6462 0.00919 0.00367 -0.0222 0.9926 0.0765
-6.250 -0.6136 0.00896 0.00347 -0.0231 0.9871 0.0808
-6.000 -0.5784 0.00878 0.00329 -0.0246 0.9814 0.0835
-5.750 -0.5445 0.00863 0.00312 -0.0257 0.9700 0.0848
-5.500 -0.5057 0.00840 0.00290 -0.0278 0.9400 0.0895
-5.250 -0.4716 0.00829 0.00269 -0.0288 0.8984 0.0933
-5.000 -0.4449 0.00825 0.00255 -0.0283 0.8687 0.0963
-4.750 -0.4185 0.00817 0.00241 -0.0277 0.8414 0.1009
-4.500 -0.3925 0.00814 0.00228 -0.0271 0.8029 0.1059
-4.250 -0.3669 0.00817 0.00215 -0.0263 0.7536 0.1118
-4.000 -0.3406 0.00818 0.00203 -0.0258 0.7115 0.1188
-3.750 -0.3134 0.00818 0.00193 -0.0254 0.6784 0.1237
-3.500 -0.2860 0.00814 0.00183 -0.0251 0.6509 0.1298
-3.250 -0.2584 0.00814 0.00174 -0.0248 0.6241 0.1343
-3.000 -0.2308 0.00814 0.00165 -0.0246 0.5959 0.1382
-2.750 -0.2031 0.00812 0.00158 -0.0243 0.5722 0.1433
-2.500 -0.1751 0.00811 0.00151 -0.0241 0.5528 0.1476
-2.250 -0.1470 0.00811 0.00145 -0.0239 0.5329 0.1507
-2.000 -0.1192 0.00811 0.00139 -0.0237 0.5103 0.1557
-1.750 -0.0913 0.00812 0.00134 -0.0235 0.4871 0.1605
-1.500 -0.0633 0.00814 0.00130 -0.0233 0.4645 0.1648
-1.250 -0.0354 0.00816 0.00126 -0.0231 0.4427 0.1692
-1.000 -0.0075 0.00818 0.00123 -0.0229 0.4199 0.1759
-0.750 0.0204 0.00823 0.00121 -0.0227 0.3939 0.1821
-0.500 0.0480 0.00827 0.00120 -0.0225 0.3646 0.1912
-0.250 0.0755 0.00836 0.00120 -0.0223 0.3302 0.2013
0.000 0.1029 0.00843 0.00121 -0.0221 0.2969 0.2184
0.250 0.1303 0.00844 0.00122 -0.0219 0.2725 0.2464
0.500 0.1577 0.00841 0.00124 -0.0217 0.2537 0.2802
0.750 0.1852 0.00835 0.00126 -0.0215 0.2390 0.3224
1.000 0.2126 0.00830 0.00129 -0.0213 0.2254 0.3678
1.250 0.2401 0.00825 0.00134 -0.0211 0.2133 0.4144
1.500 0.2678 0.00820 0.00139 -0.0209 0.2057 0.4539
1.750 0.2957 0.00821 0.00145 -0.0207 0.1986 0.4812
2.000 0.3236 0.00823 0.00151 -0.0206 0.1928 0.5045
2.250 0.3516 0.00824 0.00158 -0.0204 0.1876 0.5278
2.500 0.3794 0.00826 0.00165 -0.0202 0.1819 0.5548
3.000 0.4348 0.00824 0.00183 -0.0197 0.1743 0.6243
3.250 0.4623 0.00823 0.00193 -0.0194 0.1706 0.6636
3.500 0.4897 0.00827 0.00204 -0.0191 0.1659 0.6954
3.750 0.5171 0.00831 0.00215 -0.0188 0.1614 0.7246
4.000 0.5444 0.00831 0.00227 -0.0185 0.1588 0.7572
4.250 0.5709 0.00830 0.00239 -0.0179 0.1553 0.7993
4.500 0.5960 0.00826 0.00252 -0.0170 0.1507 0.8556
4.750 0.6193 0.00822 0.00265 -0.0157 0.1464 0.9217
5.000 0.6566 0.00828 0.00277 -0.0174 0.1425 0.9794
5.250 0.6908 0.00844 0.00290 -0.0186 0.1362 1.0000
5.500 0.7177 0.00861 0.00304 -0.0183 0.1300 1.0000
5.750 0.7442 0.00883 0.00319 -0.0179 0.1197 1.0000
6.000 0.7709 0.00905 0.00336 -0.0175 0.1111 1.0000
6.250 0.7975 0.00928 0.00355 -0.0172 0.1039 1.0000
6.500 0.8240 0.00952 0.00376 -0.0168 0.0981 1.0000
6.750 0.8506 0.00974 0.00396 -0.0165 0.0935 1.0000
7.000 0.8772 0.00996 0.00417 -0.0161 0.0889 1.0000
7.250 0.9034 0.01025 0.00442 -0.0157 0.0826 1.0000
7.500 0.9299 0.01049 0.00465 -0.0153 0.0781 1.0000
7.750 0.9558 0.01079 0.00492 -0.0149 0.0730 1.0000
8.000 0.9822 0.01103 0.00516 -0.0146 0.0691 1.0000
8.250 1.0078 0.01136 0.00546 -0.0141 0.0636 1.0000
8.500 1.0337 0.01166 0.00575 -0.0137 0.0586 1.0000
8.750 1.0589 0.01203 0.00609 -0.0133 0.0527 1.0000
9.000 1.0837 0.01246 0.00647 -0.0128 0.0461 1.0000
9.250 1.1082 0.01289 0.00687 -0.0122 0.0404 1.0000
9.500 1.1329 0.01330 0.00727 -0.0117 0.0363 1.0000
9.750 1.1574 0.01372 0.00769 -0.0112 0.0327 1.0000
10.000 1.1815 0.01418 0.00814 -0.0106 0.0295 1.0000
10.250 1.2055 0.01463 0.00859 -0.0100 0.0262 1.0000
10.500 1.2283 0.01521 0.00915 -0.0093 0.0210 1.0000
11.000 1.2695 0.01682 0.01071 -0.0075 0.0086 1.0000
11.250 1.2916 0.01739 0.01133 -0.0067 0.0078 1.0000
11.500 1.3135 0.01795 0.01193 -0.0059 0.0074 1.0000
11.750 1.3349 0.01853 0.01256 -0.0051 0.0071 1.0000
12.000 1.3555 0.01917 0.01325 -0.0042 0.0068 1.0000
12.250 1.3749 0.01988 0.01401 -0.0032 0.0065 1.0000
12.500 1.3934 0.02063 0.01482 -0.0021 0.0062 1.0000
12.750 1.4123 0.02129 0.01554 -0.0010 0.0061 1.0000
13.000 1.4298 0.02200 0.01632 0.0002 0.0059 1.0000
13.250 1.4459 0.02279 0.01717 0.0015 0.0058 1.0000
13.500 1.4607 0.02358 0.01804 0.0029 0.0057 1.0000
13.750 1.4721 0.02447 0.01900 0.0048 0.0056 1.0000
14.000 1.4789 0.02537 0.01998 0.0074 0.0055 1.0000
14.250 1.4832 0.02643 0.02111 0.0099 0.0054 1.0000
14.500 1.4860 0.02767 0.02243 0.0121 0.0053 1.0000
14.750 1.4864 0.02923 0.02408 0.0139 0.0053 1.0000
15.000 1.4854 0.03112 0.02608 0.0151 0.0052 1.0000
15.250 1.4826 0.03347 0.02853 0.0157 0.0052 1.0000
15.500 1.4771 0.03644 0.03161 0.0155 0.0051 1.0000
15.750 1.4697 0.04002 0.03531 0.0144 0.0050 1.0000
16.000 1.4582 0.04452 0.03995 0.0125 0.0050 1.0000
16.250 1.4445 0.04977 0.04534 0.0099 0.0051 1.0000
16.500 1.4197 0.05709 0.05284 0.0057 0.0050 1.0000
16.750 1.3933 0.06513 0.06106 0.0011 0.0051 1.0000
17.000 1.3523 0.07609 0.07224 -0.0053 0.0052 1.0000
17.250 1.2987 0.08967 0.08605 -0.0132 0.0052 1.0000
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Polar data table (+)
Polar graphs
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