EPPLER 426 AIRFOIL (e426-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER 426 AIRFOIL (e426-il) Reynolds number: 100,000 Max Cl/Cd: 33.44 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e426-il-100000.txt Download as CSV file: xf-e426-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.8094 0.06714 0.06185 -0.0300 1.0000 0.0841
-10.750 -0.8457 0.05984 0.05444 -0.0342 1.0000 0.0831
-10.500 -0.8818 0.05348 0.04781 -0.0352 1.0000 0.0827
-10.250 -0.9102 0.04690 0.04066 -0.0353 1.0000 0.0838
-10.000 -0.8798 0.04791 0.04197 -0.0342 1.0000 0.0895
-9.750 -0.8851 0.04379 0.03739 -0.0337 1.0000 0.0943
-9.500 -0.8709 0.04230 0.03583 -0.0328 1.0000 0.1002
-9.250 -0.8640 0.03973 0.03279 -0.0319 1.0000 0.1080
-9.000 -0.8349 0.04067 0.03408 -0.0311 1.0000 0.1155
-8.750 -0.8254 0.03809 0.03108 -0.0302 1.0000 0.1242
-8.500 -0.8037 0.03775 0.03069 -0.0293 1.0000 0.1332
-8.250 -0.7829 0.03690 0.02985 -0.0286 1.0000 0.1412
-8.000 -0.7681 0.03517 0.02759 -0.0277 1.0000 0.1504
-7.750 -0.7437 0.03449 0.02714 -0.0271 1.0000 0.1571
-7.500 -0.7254 0.03302 0.02527 -0.0263 1.0000 0.1651
-7.250 -0.7039 0.03163 0.02386 -0.0257 1.0000 0.1712
-7.000 -0.6814 0.03073 0.02285 -0.0250 1.0000 0.1781
-6.750 -0.6616 0.02913 0.02087 -0.0243 1.0000 0.1845
-6.500 -0.6377 0.02814 0.01996 -0.0236 1.0000 0.1899
-6.250 -0.6151 0.02691 0.01851 -0.0230 1.0000 0.1951
-6.000 -0.5925 0.02567 0.01683 -0.0222 1.0000 0.1992
-5.750 -0.5689 0.02417 0.01535 -0.0217 1.0000 0.2029
-5.500 -0.5450 0.02321 0.01435 -0.0210 1.0000 0.2079
-5.250 -0.5211 0.02231 0.01323 -0.0202 1.0000 0.2138
-5.000 -0.4972 0.02122 0.01208 -0.0195 1.0000 0.2190
-4.750 -0.4731 0.02037 0.01125 -0.0188 1.0000 0.2252
-4.250 -0.4252 0.01876 0.00961 -0.0172 1.0000 0.2403
-4.000 -0.4015 0.01812 0.00889 -0.0164 1.0000 0.2504
-3.750 -0.3784 0.01746 0.00837 -0.0155 1.0000 0.2608
-3.500 -0.3555 0.01684 0.00783 -0.0146 1.0000 0.2718
-3.250 -0.3329 0.01633 0.00736 -0.0137 1.0000 0.2840
-3.000 -0.3113 0.01586 0.00699 -0.0127 1.0000 0.2973
-2.750 -0.2907 0.01542 0.00671 -0.0115 1.0000 0.3125
-2.500 -0.2710 0.01506 0.00650 -0.0103 1.0000 0.3308
-2.250 -0.2527 0.01471 0.00639 -0.0090 1.0000 0.3531
-2.000 -0.2353 0.01445 0.00639 -0.0078 1.0000 0.3849
-1.750 -0.2189 0.01419 0.00651 -0.0064 1.0000 0.4350
-1.250 -0.1355 0.01367 0.00710 -0.0117 0.9734 0.6515
-1.000 -0.0799 0.01345 0.00713 -0.0157 0.9498 0.7231
-0.750 -0.0295 0.01322 0.00706 -0.0183 0.9299 0.7764
-0.500 0.0134 0.01303 0.00697 -0.0195 0.9101 0.8216
-0.250 0.0513 0.01289 0.00689 -0.0196 0.8869 0.8600
0.000 0.0926 0.01280 0.00679 -0.0203 0.8632 0.8961
0.250 0.1369 0.01276 0.00672 -0.0218 0.8338 0.9289
0.500 0.1876 0.01274 0.00658 -0.0249 0.8016 0.9577
0.750 0.2476 0.01268 0.00635 -0.0301 0.7655 0.9837
1.000 0.2912 0.01259 0.00607 -0.0329 0.7284 1.0000
1.250 0.3050 0.01261 0.00593 -0.0305 0.6954 1.0000
1.500 0.3208 0.01270 0.00582 -0.0282 0.6604 1.0000
1.750 0.3385 0.01284 0.00576 -0.0261 0.6206 1.0000
2.000 0.3574 0.01306 0.00572 -0.0240 0.5762 1.0000
2.250 0.3770 0.01338 0.00573 -0.0221 0.5253 1.0000
2.500 0.3977 0.01383 0.00582 -0.0205 0.4749 1.0000
2.750 0.4198 0.01432 0.00601 -0.0192 0.4334 1.0000
3.000 0.4431 0.01484 0.00626 -0.0182 0.4038 1.0000
3.250 0.4672 0.01533 0.00656 -0.0174 0.3796 1.0000
3.500 0.4919 0.01584 0.00688 -0.0167 0.3606 1.0000
3.750 0.5170 0.01635 0.00728 -0.0161 0.3445 1.0000
4.000 0.5424 0.01689 0.00772 -0.0155 0.3304 1.0000
4.250 0.5679 0.01746 0.00822 -0.0150 0.3179 1.0000
4.500 0.5937 0.01810 0.00872 -0.0145 0.3071 1.0000
4.750 0.6194 0.01869 0.00931 -0.0140 0.2960 1.0000
5.000 0.6451 0.01937 0.01000 -0.0136 0.2856 1.0000
5.250 0.6711 0.02015 0.01061 -0.0132 0.2761 1.0000
5.500 0.6963 0.02082 0.01145 -0.0126 0.2662 1.0000
5.750 0.7220 0.02169 0.01224 -0.0122 0.2575 1.0000
6.000 0.7469 0.02242 0.01309 -0.0116 0.2478 1.0000
6.250 0.7720 0.02341 0.01410 -0.0112 0.2396 1.0000
6.500 0.7966 0.02423 0.01501 -0.0106 0.2309 1.0000
6.750 0.8210 0.02532 0.01617 -0.0101 0.2231 1.0000
7.000 0.8450 0.02621 0.01718 -0.0095 0.2149 1.0000
7.250 0.8689 0.02739 0.01839 -0.0090 0.2080 1.0000
7.500 0.8916 0.02835 0.01958 -0.0082 0.1998 1.0000
7.750 0.9163 0.02954 0.02064 -0.0079 0.1934 1.0000
8.000 0.9360 0.03068 0.02221 -0.0068 0.1855 1.0000
8.250 0.9606 0.03152 0.02296 -0.0064 0.1791 1.0000
8.500 0.9784 0.03316 0.02498 -0.0054 0.1721 1.0000
8.750 1.0009 0.03405 0.02593 -0.0047 0.1655 1.0000
9.000 1.0208 0.03561 0.02759 -0.0040 0.1599 1.0000
9.250 1.0360 0.03738 0.02975 -0.0028 0.1534 1.0000
9.500 1.0609 0.03806 0.03031 -0.0023 0.1483 1.0000
9.750 1.0695 0.04082 0.03353 -0.0010 0.1432 1.0000
10.000 1.0817 0.04291 0.03591 0.0002 0.1382 1.0000
10.250 1.1069 0.04364 0.03653 0.0006 0.1341 1.0000
10.500 1.1070 0.04733 0.04066 0.0020 0.1309 1.0000
10.750 1.0916 0.05221 0.04609 0.0037 0.1281 1.0000
11.000 1.0711 0.05721 0.05145 0.0048 0.1262 1.0000
11.500 1.0656 0.06269 0.05713 0.0068 0.1219 1.0000
11.750 1.0481 0.06692 0.06147 0.0070 0.1210 1.0000
12.000 1.0378 0.07135 0.06594 0.0064 0.1199 1.0000
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Polar data table (+)
Polar graphs
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