EPPLER 426 AIRFOIL (e426-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 426 AIRFOIL (e426-il) Reynolds number: 200,000 Max Cl/Cd: 48.21 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e426-il-200000.txt Download as CSV file: xf-e426-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.8712 0.10467 0.10063 -0.0037 1.0000 0.0356
-14.500 -0.9269 0.08889 0.08468 -0.0142 1.0000 0.0348
-14.250 -0.9682 0.07682 0.07239 -0.0229 1.0000 0.0341
-14.000 -0.9994 0.06741 0.06277 -0.0301 1.0000 0.0338
-13.750 -1.0227 0.06005 0.05519 -0.0356 1.0000 0.0337
-13.500 -1.0408 0.05408 0.04900 -0.0397 1.0000 0.0338
-13.250 -1.0541 0.04932 0.04403 -0.0426 1.0000 0.0339
-13.000 -1.0649 0.04536 0.03987 -0.0443 1.0000 0.0342
-12.750 -1.0731 0.04214 0.03645 -0.0449 1.0000 0.0346
-12.500 -1.0793 0.03953 0.03362 -0.0442 1.0000 0.0350
-12.250 -1.0833 0.03737 0.03124 -0.0425 1.0000 0.0354
-12.000 -1.0803 0.03499 0.02875 -0.0410 1.0000 0.0362
-11.750 -1.0720 0.03314 0.02689 -0.0398 1.0000 0.0373
-11.500 -1.0617 0.03155 0.02524 -0.0386 1.0000 0.0388
-11.250 -1.0501 0.02995 0.02345 -0.0374 1.0000 0.0407
-11.000 -1.0382 0.02818 0.02160 -0.0362 1.0000 0.0427
-10.750 -1.0229 0.02691 0.02032 -0.0351 1.0000 0.0453
-10.500 -1.0066 0.02553 0.01877 -0.0340 1.0000 0.0486
-10.250 -0.9887 0.02449 0.01777 -0.0331 1.0000 0.0524
-10.000 -0.9693 0.02353 0.01675 -0.0323 1.0000 0.0577
-9.750 -0.9481 0.02284 0.01596 -0.0315 1.0000 0.0649
-9.500 -0.9260 0.02241 0.01541 -0.0308 1.0000 0.0733
-9.250 -0.9048 0.02181 0.01485 -0.0301 1.0000 0.0820
-9.000 -0.8826 0.02137 0.01439 -0.0294 1.0000 0.0906
-8.750 -0.8598 0.02103 0.01393 -0.0287 1.0000 0.0988
-8.500 -0.8356 0.02110 0.01398 -0.0281 1.0000 0.1058
-8.250 -0.8121 0.02082 0.01364 -0.0275 1.0000 0.1120
-8.000 -0.7876 0.02085 0.01365 -0.0268 1.0000 0.1179
-7.750 -0.7639 0.02041 0.01303 -0.0261 1.0000 0.1231
-7.500 -0.7393 0.02017 0.01286 -0.0256 1.0000 0.1277
-7.250 -0.7149 0.01991 0.01250 -0.0249 1.0000 0.1326
-7.000 -0.6907 0.01942 0.01183 -0.0242 1.0000 0.1366
-6.750 -0.6664 0.01881 0.01130 -0.0236 1.0000 0.1407
-6.500 -0.6419 0.01855 0.01101 -0.0229 1.0000 0.1455
-6.250 -0.6173 0.01832 0.01062 -0.0221 1.0000 0.1503
-6.000 -0.5933 0.01746 0.00979 -0.0214 1.0000 0.1544
-5.750 -0.5688 0.01691 0.00924 -0.0207 1.0000 0.1577
-5.500 -0.5443 0.01640 0.00869 -0.0199 1.0000 0.1615
-5.250 -0.5197 0.01596 0.00814 -0.0191 1.0000 0.1655
-5.000 -0.4958 0.01525 0.00747 -0.0184 1.0000 0.1703
-4.750 -0.4718 0.01483 0.00710 -0.0176 1.0000 0.1758
-4.500 -0.4476 0.01449 0.00668 -0.0167 1.0000 0.1820
-4.250 -0.4244 0.01388 0.00618 -0.0158 1.0000 0.1884
-4.000 -0.4011 0.01355 0.00587 -0.0149 1.0000 0.1960
-3.750 -0.3786 0.01312 0.00549 -0.0139 1.0000 0.2036
-3.500 -0.3567 0.01284 0.00526 -0.0129 1.0000 0.2118
-3.250 -0.3359 0.01253 0.00502 -0.0117 1.0000 0.2199
-3.000 -0.3164 0.01234 0.00489 -0.0104 1.0000 0.2288
-2.750 -0.2792 0.01206 0.00472 -0.0127 0.9941 0.2413
-2.500 -0.2293 0.01170 0.00449 -0.0172 0.9830 0.2584
-2.250 -0.1802 0.01125 0.00420 -0.0213 0.9671 0.2809
-2.000 -0.1355 0.01070 0.00391 -0.0244 0.9463 0.3171
-1.750 -0.0933 0.01005 0.00371 -0.0271 0.9236 0.4024
-1.500 -0.0558 0.00959 0.00364 -0.0285 0.8986 0.5043
-1.250 -0.0255 0.00939 0.00362 -0.0283 0.8706 0.5707
-1.000 0.0009 0.00931 0.00363 -0.0272 0.8419 0.6193
-0.750 0.0259 0.00928 0.00363 -0.0258 0.8140 0.6565
-0.500 0.0506 0.00926 0.00363 -0.0245 0.7871 0.6893
-0.250 0.0752 0.00927 0.00362 -0.0231 0.7621 0.7206
0.000 0.0995 0.00925 0.00363 -0.0216 0.7365 0.7511
0.250 0.1233 0.00926 0.00363 -0.0200 0.7116 0.7826
0.500 0.1470 0.00925 0.00364 -0.0184 0.6854 0.8148
0.750 0.1705 0.00927 0.00363 -0.0167 0.6598 0.8482
1.000 0.1959 0.00927 0.00364 -0.0154 0.6323 0.8831
1.250 0.2274 0.00934 0.00363 -0.0153 0.6021 0.9189
1.500 0.2672 0.00946 0.00363 -0.0172 0.5650 0.9543
1.750 0.3152 0.00965 0.00360 -0.0209 0.5143 0.9848
2.000 0.3545 0.00993 0.00356 -0.0233 0.4524 1.0000
2.250 0.3737 0.01027 0.00359 -0.0218 0.3984 1.0000
2.500 0.3945 0.01068 0.00369 -0.0206 0.3555 1.0000
2.750 0.4171 0.01108 0.00385 -0.0196 0.3265 1.0000
3.000 0.4407 0.01146 0.00405 -0.0188 0.3072 1.0000
3.500 0.4902 0.01217 0.00453 -0.0175 0.2803 1.0000
3.750 0.5155 0.01255 0.00483 -0.0169 0.2705 1.0000
4.000 0.5407 0.01295 0.00512 -0.0164 0.2613 1.0000
4.250 0.5666 0.01329 0.00545 -0.0159 0.2526 1.0000
4.500 0.5922 0.01372 0.00578 -0.0154 0.2449 1.0000
4.750 0.6183 0.01409 0.00617 -0.0149 0.2376 1.0000
5.000 0.6441 0.01447 0.00651 -0.0144 0.2301 1.0000
5.250 0.6700 0.01493 0.00695 -0.0140 0.2228 1.0000
5.500 0.6959 0.01528 0.00731 -0.0135 0.2154 1.0000
5.750 0.7216 0.01585 0.00782 -0.0131 0.2086 1.0000
6.000 0.7475 0.01615 0.00821 -0.0126 0.2010 1.0000
6.250 0.7729 0.01678 0.00872 -0.0122 0.1941 1.0000
6.500 0.7985 0.01710 0.00919 -0.0116 0.1872 1.0000
6.750 0.8240 0.01750 0.00956 -0.0112 0.1805 1.0000
7.000 0.8491 0.01807 0.01018 -0.0107 0.1739 1.0000
7.250 0.8743 0.01839 0.01055 -0.0101 0.1670 1.0000
7.500 0.8991 0.01903 0.01112 -0.0097 0.1609 1.0000
7.750 0.9239 0.01932 0.01158 -0.0091 0.1544 1.0000
8.000 0.9485 0.01973 0.01194 -0.0086 0.1488 1.0000
8.250 0.9727 0.02032 0.01265 -0.0080 0.1431 1.0000
8.500 0.9970 0.02068 0.01307 -0.0073 0.1373 1.0000
8.750 1.0208 0.02135 0.01368 -0.0068 0.1322 1.0000
9.000 1.0442 0.02179 0.01433 -0.0061 0.1265 1.0000
9.250 1.0675 0.02221 0.01471 -0.0054 0.1213 1.0000
9.500 1.0898 0.02284 0.01547 -0.0047 0.1155 1.0000
9.750 1.1121 0.02317 0.01581 -0.0039 0.1097 1.0000
10.000 1.1332 0.02396 0.01667 -0.0031 0.1044 1.0000
10.250 1.1544 0.02448 0.01729 -0.0023 0.0991 1.0000
10.500 1.1745 0.02549 0.01821 -0.0015 0.0946 1.0000
10.750 1.1938 0.02618 0.01915 -0.0005 0.0903 1.0000
11.000 1.2130 0.02681 0.01982 0.0004 0.0861 1.0000
11.250 1.2305 0.02787 0.02090 0.0014 0.0822 1.0000
11.500 1.2474 0.02856 0.02180 0.0026 0.0782 1.0000
11.750 1.2638 0.02926 0.02254 0.0037 0.0749 1.0000
12.000 1.2778 0.03038 0.02371 0.0050 0.0718 1.0000
12.250 1.2904 0.03120 0.02475 0.0065 0.0683 1.0000
12.500 1.3015 0.03199 0.02561 0.0081 0.0654 1.0000
12.750 1.3074 0.03322 0.02683 0.0101 0.0629 1.0000
13.000 1.3108 0.03440 0.02827 0.0121 0.0600 1.0000
13.250 1.3138 0.03563 0.02960 0.0136 0.0570 1.0000
13.500 1.3134 0.03751 0.03146 0.0147 0.0547 1.0000
13.750 1.3111 0.03975 0.03399 0.0150 0.0512 1.0000
14.000 1.3077 0.04239 0.03671 0.0146 0.0484 1.0000
14.250 1.2988 0.04609 0.04055 0.0134 0.0455 1.0000
14.500 1.2900 0.05020 0.04481 0.0115 0.0429 1.0000
14.750 1.2772 0.05507 0.04972 0.0089 0.0410 1.0000
15.000 1.2610 0.06089 0.05572 0.0057 0.0392 1.0000
15.250 1.2443 0.06711 0.06211 0.0021 0.0377 1.0000
15.500 1.2275 0.07356 0.06868 -0.0017 0.0366 1.0000
15.750 1.2103 0.08019 0.07540 -0.0056 0.0357 1.0000
16.000 1.1956 0.08628 0.08148 -0.0089 0.0345 1.0000
16.250 1.1765 0.09385 0.08924 -0.0133 0.0340 1.0000
16.500 1.1555 0.10214 0.09770 -0.0183 0.0333 1.0000
16.750 1.1373 0.10997 0.10568 -0.0229 0.0327 1.0000
17.000 1.1179 0.11834 0.11419 -0.0278 0.0322 1.0000
17.250 1.0981 0.12710 0.12307 -0.0332 0.0315 1.0000
17.500 1.0736 0.13721 0.13333 -0.0393 0.0312 1.0000
17.750 1.0988 0.13507 0.13097 -0.0373 0.0293 1.0000
18.000 1.0714 0.14627 0.14236 -0.0444 0.0293 1.0000
18.250 0.6749 0.20931 0.20619 -0.0766 0.0519 1.0000
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Polar data table (+)
Polar graphs
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