EPPLER 426 AIRFOIL (e426-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 426 AIRFOIL (e426-il) Reynolds number: 500,000 Max Cl/Cd: 74.36 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e426-il-500000-n5.txt Download as CSV file: xf-e426-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -1.0554 0.08334 0.07944 -0.0127 1.0000 0.0123
-15.250 -1.0988 0.07230 0.06827 -0.0192 1.0000 0.0122
-15.000 -1.1463 0.06015 0.05593 -0.0268 1.0000 0.0120
-14.750 -1.1823 0.04989 0.04544 -0.0339 1.0000 0.0119
-14.500 -1.2033 0.04273 0.03808 -0.0392 1.0000 0.0120
-14.250 -1.2166 0.03761 0.03279 -0.0427 1.0000 0.0120
-14.000 -1.2250 0.03401 0.02904 -0.0443 1.0000 0.0121
-13.750 -1.2309 0.03146 0.02635 -0.0442 1.0000 0.0122
-13.500 -1.2333 0.02971 0.02448 -0.0426 1.0000 0.0123
-13.250 -1.2326 0.02820 0.02287 -0.0405 1.0000 0.0125
-13.000 -1.2251 0.02675 0.02133 -0.0390 1.0000 0.0128
-12.750 -1.2132 0.02554 0.02003 -0.0379 1.0000 0.0131
-12.500 -1.1985 0.02448 0.01888 -0.0368 1.0000 0.0135
-12.250 -1.1818 0.02353 0.01783 -0.0358 1.0000 0.0140
-12.000 -1.1639 0.02265 0.01686 -0.0349 1.0000 0.0146
-11.750 -1.1447 0.02184 0.01596 -0.0341 1.0000 0.0151
-11.500 -1.1262 0.02089 0.01495 -0.0332 1.0000 0.0158
-11.250 -1.1060 0.02009 0.01409 -0.0324 1.0000 0.0166
-11.000 -1.0848 0.01939 0.01330 -0.0317 1.0000 0.0175
-10.750 -1.0631 0.01871 0.01255 -0.0309 1.0000 0.0185
-10.500 -1.0415 0.01799 0.01179 -0.0302 1.0000 0.0198
-10.250 -1.0188 0.01739 0.01114 -0.0295 1.0000 0.0213
-10.000 -0.9962 0.01677 0.01046 -0.0289 1.0000 0.0231
-9.750 -0.9730 0.01621 0.00986 -0.0282 1.0000 0.0254
-9.500 -0.9500 0.01561 0.00924 -0.0275 1.0000 0.0282
-9.250 -0.9266 0.01506 0.00866 -0.0268 1.0000 0.0316
-8.500 -0.8565 0.01337 0.00707 -0.0248 1.0000 0.0542
-8.250 -0.8318 0.01304 0.00675 -0.0242 1.0000 0.0631
-8.000 -0.8070 0.01273 0.00645 -0.0236 1.0000 0.0686
-7.750 -0.7817 0.01250 0.00618 -0.0230 1.0000 0.0728
-7.500 -0.7569 0.01220 0.00588 -0.0223 1.0000 0.0763
-7.250 -0.7320 0.01192 0.00560 -0.0217 1.0000 0.0801
-7.000 -0.7068 0.01170 0.00535 -0.0210 1.0000 0.0837
-6.750 -0.6819 0.01143 0.00508 -0.0203 1.0000 0.0874
-6.500 -0.6571 0.01117 0.00484 -0.0197 1.0000 0.0913
-6.250 -0.6320 0.01094 0.00460 -0.0190 1.0000 0.0942
-6.000 -0.6069 0.01074 0.00438 -0.0183 1.0000 0.0966
-5.750 -0.5821 0.01049 0.00416 -0.0176 1.0000 0.1010
-5.500 -0.5475 0.01027 0.00396 -0.0189 0.9956 0.1059
-5.250 -0.5128 0.01007 0.00376 -0.0203 0.9891 0.1100
-5.000 -0.4770 0.00985 0.00357 -0.0218 0.9816 0.1151
-4.500 -0.4075 0.00947 0.00322 -0.0244 0.9488 0.1268
-4.250 -0.3652 0.00930 0.00303 -0.0272 0.9236 0.1334
-4.000 -0.3290 0.00919 0.00284 -0.0286 0.8928 0.1387
-3.750 -0.3013 0.00915 0.00270 -0.0282 0.8533 0.1442
-3.500 -0.2759 0.00920 0.00257 -0.0272 0.8033 0.1488
-3.250 -0.2504 0.00924 0.00243 -0.0264 0.7604 0.1531
-3.000 -0.2242 0.00923 0.00231 -0.0258 0.7271 0.1583
-2.750 -0.1974 0.00923 0.00220 -0.0253 0.6962 0.1633
-2.500 -0.1705 0.00925 0.00209 -0.0248 0.6653 0.1676
-2.250 -0.1435 0.00921 0.00199 -0.0244 0.6389 0.1734
-2.000 -0.1160 0.00919 0.00191 -0.0241 0.6171 0.1793
-1.750 -0.0885 0.00917 0.00183 -0.0238 0.5957 0.1857
-1.500 -0.0611 0.00914 0.00176 -0.0235 0.5747 0.1942
-1.250 -0.0337 0.00911 0.00170 -0.0232 0.5523 0.2043
-1.000 -0.0063 0.00910 0.00164 -0.0230 0.5274 0.2165
-0.750 0.0210 0.00908 0.00159 -0.0227 0.5025 0.2322
-0.500 0.0481 0.00900 0.00155 -0.0224 0.4783 0.2611
-0.250 0.0749 0.00887 0.00151 -0.0222 0.4541 0.3092
0.000 0.1017 0.00876 0.00150 -0.0219 0.4274 0.3617
0.250 0.1285 0.00871 0.00152 -0.0216 0.3983 0.4127
0.500 0.1552 0.00872 0.00155 -0.0213 0.3646 0.4561
0.750 0.1820 0.00880 0.00160 -0.0210 0.3281 0.4905
1.000 0.2088 0.00892 0.00166 -0.0206 0.2948 0.5178
1.250 0.2358 0.00902 0.00174 -0.0203 0.2704 0.5446
1.500 0.2629 0.00908 0.00183 -0.0200 0.2533 0.5733
1.750 0.2899 0.00915 0.00193 -0.0197 0.2387 0.6038
2.000 0.3169 0.00923 0.00203 -0.0194 0.2259 0.6330
2.250 0.3441 0.00926 0.00213 -0.0190 0.2170 0.6619
2.500 0.3709 0.00930 0.00225 -0.0186 0.2100 0.6978
2.750 0.3976 0.00930 0.00237 -0.0181 0.2044 0.7339
3.000 0.4238 0.00932 0.00250 -0.0175 0.1979 0.7695
3.250 0.4494 0.00934 0.00263 -0.0167 0.1923 0.8096
3.500 0.4741 0.00930 0.00276 -0.0156 0.1879 0.8573
3.750 0.5008 0.00928 0.00289 -0.0148 0.1831 0.9257
4.000 0.5447 0.00943 0.00304 -0.0180 0.1772 0.9873
4.250 0.5761 0.00957 0.00317 -0.0186 0.1728 1.0000
4.500 0.6026 0.00973 0.00331 -0.0182 0.1681 1.0000
4.750 0.6291 0.00993 0.00347 -0.0178 0.1636 1.0000
5.000 0.6558 0.01010 0.00365 -0.0174 0.1597 1.0000
5.250 0.6827 0.01026 0.00381 -0.0170 0.1548 1.0000
5.500 0.7093 0.01047 0.00398 -0.0167 0.1498 1.0000
5.750 0.7359 0.01067 0.00418 -0.0163 0.1452 1.0000
6.000 0.7627 0.01085 0.00437 -0.0159 0.1396 1.0000
6.250 0.7890 0.01110 0.00457 -0.0155 0.1326 1.0000
6.500 0.8156 0.01130 0.00477 -0.0152 0.1249 1.0000
6.750 0.8418 0.01157 0.00500 -0.0148 0.1178 1.0000
7.000 0.8681 0.01183 0.00525 -0.0144 0.1116 1.0000
7.250 0.8939 0.01213 0.00552 -0.0140 0.1054 1.0000
7.500 0.9199 0.01242 0.00581 -0.0136 0.1000 1.0000
7.750 0.9453 0.01277 0.00613 -0.0131 0.0944 1.0000
8.000 0.9711 0.01306 0.00645 -0.0127 0.0895 1.0000
8.250 0.9961 0.01346 0.00681 -0.0122 0.0837 1.0000
8.500 1.0217 0.01376 0.00714 -0.0118 0.0791 1.0000
8.750 1.0465 0.01415 0.00753 -0.0113 0.0740 1.0000
9.000 1.0715 0.01451 0.00791 -0.0108 0.0697 1.0000
9.250 1.0961 0.01492 0.00831 -0.0103 0.0646 1.0000
9.500 1.1204 0.01534 0.00874 -0.0097 0.0598 1.0000
9.750 1.1441 0.01583 0.00922 -0.0092 0.0549 1.0000
10.000 1.1681 0.01627 0.00969 -0.0086 0.0509 1.0000
10.250 1.1910 0.01682 0.01023 -0.0079 0.0464 1.0000
10.500 1.2138 0.01735 0.01079 -0.0073 0.0422 1.0000
10.750 1.2360 0.01794 0.01138 -0.0065 0.0382 1.0000
11.000 1.2573 0.01859 0.01204 -0.0057 0.0344 1.0000
11.250 1.2790 0.01917 0.01266 -0.0050 0.0315 1.0000
11.500 1.2995 0.01985 0.01338 -0.0041 0.0283 1.0000
11.750 1.3189 0.02060 0.01415 -0.0031 0.0243 1.0000
12.000 1.3368 0.02146 0.01502 -0.0020 0.0184 1.0000
12.250 1.3501 0.02269 0.01623 -0.0006 0.0121 1.0000
12.500 1.3640 0.02377 0.01735 0.0009 0.0106 1.0000
12.750 1.3775 0.02477 0.01844 0.0024 0.0099 1.0000
13.000 1.3894 0.02580 0.01957 0.0040 0.0093 1.0000
13.250 1.3964 0.02688 0.02073 0.0064 0.0090 1.0000
13.500 1.4013 0.02801 0.02196 0.0087 0.0088 1.0000
13.750 1.4024 0.02948 0.02353 0.0109 0.0085 1.0000
14.000 1.4025 0.03118 0.02535 0.0126 0.0084 1.0000
14.250 1.3992 0.03341 0.02770 0.0136 0.0082 1.0000
14.500 1.3946 0.03612 0.03053 0.0137 0.0080 1.0000
14.750 1.3882 0.03942 0.03398 0.0131 0.0079 1.0000
15.000 1.3802 0.04332 0.03803 0.0116 0.0079 1.0000
15.250 1.3693 0.04803 0.04289 0.0093 0.0078 1.0000
15.500 1.3536 0.05384 0.04888 0.0061 0.0078 1.0000
15.750 1.3305 0.06123 0.05645 0.0018 0.0078 1.0000
16.000 1.2997 0.07033 0.06575 -0.0036 0.0078 1.0000
16.250 1.2628 0.08086 0.07647 -0.0097 0.0080 1.0000
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Polar data table (+)
Polar graphs
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