EPPLER 635 AIRFOIL (e635-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 635 AIRFOIL (e635-il) Reynolds number: 100,000 Max Cl/Cd: 43.37 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e635-il-100000-n5.txt Download as CSV file: xf-e635-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 635 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3979 0.10562 0.10159 0.0057 1.0000 0.0519
-9.750 -0.3965 0.10156 0.09757 0.0044 1.0000 0.0525
-9.500 -0.5033 0.10088 0.09658 0.0002 1.0000 0.0500
-9.250 -0.4970 0.09702 0.09275 0.0001 1.0000 0.0506
-9.000 -0.4968 0.09279 0.08857 -0.0021 1.0000 0.0510
-8.750 -0.5003 0.08826 0.08410 -0.0051 1.0000 0.0513
-8.250 -0.5130 0.07780 0.07359 -0.0085 1.0000 0.0359
-8.000 -0.5338 0.07094 0.06656 -0.0092 1.0000 0.0291
-7.750 -0.5350 0.06725 0.06282 -0.0086 1.0000 0.0288
-7.500 -0.5359 0.06333 0.05878 -0.0078 1.0000 0.0288
-7.250 -0.5356 0.05922 0.05448 -0.0066 1.0000 0.0291
-7.000 -0.5323 0.05538 0.05044 -0.0051 1.0000 0.0292
-6.750 -0.5199 0.05118 0.04595 -0.0050 0.9143 0.0291
-6.500 -0.5043 0.04731 0.04165 -0.0045 0.8524 0.0288
-6.250 -0.4946 0.04413 0.03805 -0.0021 0.8142 0.0285
-6.000 -0.4842 0.04104 0.03449 0.0006 0.7859 0.0283
-5.750 -0.4716 0.03815 0.03112 0.0032 0.7626 0.0283
-5.500 -0.4566 0.03540 0.02783 0.0057 0.7417 0.0285
-5.250 -0.4391 0.03315 0.02488 0.0084 0.7229 0.0298
-5.000 -0.4204 0.03105 0.02256 0.0097 0.7050 0.0312
-4.750 -0.3985 0.02932 0.02050 0.0110 0.6884 0.0321
-4.500 -0.3747 0.02754 0.01834 0.0123 0.6727 0.0327
-4.250 -0.3491 0.02594 0.01639 0.0132 0.6578 0.0336
-4.000 -0.3229 0.02472 0.01486 0.0140 0.6434 0.0358
-3.750 -0.2955 0.02364 0.01344 0.0147 0.6296 0.0379
-3.500 -0.2675 0.02233 0.01196 0.0150 0.6165 0.0390
-3.250 -0.2410 0.02122 0.01079 0.0155 0.6042 0.0405
-3.000 -0.2154 0.02042 0.00988 0.0161 0.5926 0.0423
-2.750 -0.1905 0.01984 0.00919 0.0169 0.5816 0.0464
-2.500 -0.1663 0.01926 0.00848 0.0179 0.5704 0.0493
-2.250 -0.1433 0.01863 0.00778 0.0191 0.5605 0.0529
-2.000 -0.1193 0.01821 0.00720 0.0201 0.5512 0.0581
-1.750 -0.0946 0.01776 0.00672 0.0209 0.5411 0.0695
-1.500 0.0041 0.01518 0.00724 0.0087 0.5267 0.8859
-1.250 0.1521 0.01664 0.00805 -0.0121 0.5086 0.9922
-1.000 0.1873 0.01646 0.00764 -0.0138 0.4996 0.9970
-0.750 0.2178 0.01634 0.00732 -0.0147 0.4918 1.0000
-0.500 0.2408 0.01633 0.00716 -0.0140 0.4842 1.0000
-0.250 0.2638 0.01634 0.00700 -0.0133 0.4772 1.0000
0.000 0.2871 0.01636 0.00691 -0.0126 0.4703 1.0000
0.250 0.3104 0.01639 0.00682 -0.0120 0.4637 1.0000
0.500 0.3337 0.01645 0.00675 -0.0113 0.4576 1.0000
0.750 0.3573 0.01650 0.00674 -0.0107 0.4508 1.0000
1.000 0.3806 0.01658 0.00668 -0.0100 0.4456 1.0000
1.250 0.4044 0.01667 0.00674 -0.0094 0.4390 1.0000
1.500 0.4280 0.01677 0.00675 -0.0088 0.4334 1.0000
1.750 0.4517 0.01689 0.00680 -0.0081 0.4281 1.0000
2.000 0.4755 0.01702 0.00691 -0.0076 0.4221 1.0000
2.250 0.4992 0.01715 0.00697 -0.0069 0.4173 1.0000
2.500 0.5230 0.01731 0.00711 -0.0063 0.4120 1.0000
2.750 0.5468 0.01747 0.00728 -0.0058 0.4065 1.0000
3.000 0.5704 0.01763 0.00737 -0.0051 0.4020 1.0000
3.250 0.5942 0.01783 0.00760 -0.0046 0.3970 1.0000
3.500 0.6179 0.01804 0.00783 -0.0040 0.3918 1.0000
3.750 0.6415 0.01822 0.00798 -0.0033 0.3874 1.0000
4.000 0.6651 0.01847 0.00827 -0.0027 0.3827 1.0000
4.250 0.6885 0.01873 0.00859 -0.0021 0.3776 1.0000
4.500 0.7119 0.01897 0.00884 -0.0015 0.3735 1.0000
4.750 0.7351 0.01924 0.00913 -0.0008 0.3693 1.0000
5.000 0.7581 0.01956 0.00956 -0.0002 0.3640 1.0000
5.250 0.7812 0.01984 0.00988 0.0005 0.3598 1.0000
5.500 0.8044 0.02011 0.01014 0.0012 0.3564 1.0000
5.750 0.8266 0.02054 0.01075 0.0018 0.3510 1.0000
6.000 0.8491 0.02087 0.01116 0.0026 0.3463 1.0000
6.250 0.8720 0.02115 0.01144 0.0033 0.3426 1.0000
6.500 0.8937 0.02161 0.01209 0.0041 0.3377 1.0000
6.750 0.9154 0.02201 0.01262 0.0049 0.3326 1.0000
7.000 0.9379 0.02229 0.01291 0.0057 0.3284 1.0000
7.250 0.9588 0.02276 0.01355 0.0065 0.3230 1.0000
7.500 0.9797 0.02316 0.01411 0.0074 0.3174 1.0000
7.750 1.0019 0.02339 0.01435 0.0083 0.3130 1.0000
8.000 1.0210 0.02397 0.01517 0.0093 0.3065 1.0000
8.250 1.0417 0.02428 0.01557 0.0103 0.3009 1.0000
8.500 1.0617 0.02469 0.01612 0.0113 0.2953 1.0000
8.750 1.0802 0.02516 0.01678 0.0124 0.2885 1.0000
9.000 1.1008 0.02538 0.01704 0.0135 0.2829 1.0000
9.250 1.1170 0.02601 0.01793 0.0148 0.2752 1.0000
9.500 1.1366 0.02622 0.01817 0.0160 0.2690 1.0000
9.750 1.1510 0.02689 0.01914 0.0175 0.2606 1.0000
10.000 1.1677 0.02726 0.01961 0.0189 0.2533 1.0000
10.250 1.1811 0.02786 0.02039 0.0205 0.2443 1.0000
10.500 1.1932 0.02851 0.02122 0.0223 0.2354 1.0000
10.750 1.2052 0.02903 0.02181 0.0241 0.2267 1.0000
11.000 1.2119 0.02996 0.02292 0.0263 0.2166 1.0000
11.250 1.2162 0.03096 0.02409 0.0286 0.2069 1.0000
11.500 1.2172 0.03205 0.02523 0.0311 0.1978 1.0000
11.750 1.2084 0.03350 0.02679 0.0346 0.1895 1.0000
12.000 1.1962 0.03545 0.02881 0.0371 0.1823 1.0000
12.250 1.1840 0.03803 0.03146 0.0382 0.1748 1.0000
12.500 1.1709 0.04128 0.03480 0.0384 0.1673 1.0000
12.750 1.1575 0.04482 0.03834 0.0381 0.1599 1.0000
13.000 1.1416 0.04906 0.04268 0.0373 0.1527 1.0000
13.250 1.1285 0.05296 0.04654 0.0365 0.1460 1.0000
13.500 1.1124 0.05757 0.05125 0.0353 0.1393 1.0000
13.750 1.1012 0.06145 0.05507 0.0345 0.1329 1.0000
14.000 1.0871 0.06601 0.05975 0.0333 0.1267 1.0000
14.250 1.0778 0.06978 0.06347 0.0324 0.1207 1.0000
14.500 1.0655 0.07437 0.06815 0.0310 0.1147 1.0000
14.750 1.0574 0.07832 0.07208 0.0299 0.1088 1.0000
15.000 1.0486 0.08263 0.07645 0.0286 0.1033 1.0000
15.250 1.0408 0.08682 0.08068 0.0273 0.0979 1.0000
15.500 1.0361 0.09054 0.08439 0.0262 0.0930 1.0000
15.750 1.0268 0.09526 0.08923 0.0245 0.0880 1.0000
16.000 1.0245 0.09862 0.09253 0.0235 0.0832 1.0000
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Polar data table (+)
Polar graphs
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