EPPLER 341 AIRFOIL (e341-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 341 AIRFOIL (e341-il) Reynolds number: 200,000 Max Cl/Cd: 59.09 at α=11° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e341-il-200000.txt Download as CSV file: xf-e341-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 341 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4867 0.09635 0.09323 -0.0184 1.0000 0.0410
-9.500 -0.5035 0.09140 0.08820 -0.0220 1.0000 0.0410
-9.250 -0.5229 0.08763 0.08435 -0.0226 1.0000 0.0411
-9.000 -0.4987 0.08239 0.07931 -0.0218 1.0000 0.0420
-8.750 -0.4965 0.07925 0.07621 -0.0214 1.0000 0.0425
-8.500 -0.5000 0.07596 0.07292 -0.0212 1.0000 0.0431
-8.250 -0.5053 0.07279 0.06974 -0.0205 1.0000 0.0437
-8.000 -0.5090 0.06961 0.06653 -0.0197 1.0000 0.0445
-7.750 -0.5108 0.06634 0.06321 -0.0188 1.0000 0.0455
-7.500 -0.5118 0.06307 0.05984 -0.0177 1.0000 0.0471
-7.250 -0.5142 0.05917 0.05510 -0.0175 0.9061 0.0504
-7.000 -0.4980 0.05446 0.05039 -0.0174 0.8518 0.0514
-6.750 -0.4878 0.05207 0.04784 -0.0155 0.8141 0.0525
-6.500 -0.4771 0.04988 0.04543 -0.0137 0.7853 0.0543
-6.250 -0.4655 0.04772 0.04295 -0.0116 0.7626 0.0574
-6.000 -0.4600 0.04500 0.03962 -0.0083 0.7445 0.0621
-5.750 -0.4432 0.04234 0.03690 -0.0074 0.7257 0.0638
-5.500 -0.4263 0.04038 0.03476 -0.0060 0.7086 0.0667
-5.250 -0.4136 0.03872 0.03251 -0.0031 0.6941 0.0747
-5.000 -0.3940 0.03619 0.02994 -0.0023 0.6792 0.0772
-4.500 -0.3410 0.02581 0.01778 0.0045 0.6569 0.0320
-4.250 -0.3127 0.02323 0.01473 0.0056 0.6450 0.0293
-4.000 -0.2831 0.02159 0.01265 0.0063 0.6331 0.0283
-3.750 -0.2535 0.02026 0.01119 0.0064 0.6203 0.0286
-3.500 -0.2252 0.01922 0.01007 0.0066 0.6085 0.0296
-3.250 -0.1983 0.01852 0.00925 0.0071 0.5982 0.0319
-3.000 -0.1725 0.01770 0.00840 0.0077 0.5869 0.0354
-2.750 -0.1480 0.01708 0.00775 0.0085 0.5776 0.0392
-2.500 -0.1258 0.01632 0.00696 0.0098 0.5685 0.0446
-2.250 -0.1042 0.01563 0.00631 0.0113 0.5597 0.0639
-2.000 -0.0768 0.01344 0.00751 0.0137 0.5515 0.8465
-1.750 -0.0068 0.01638 0.01015 0.0102 0.5394 0.9183
-1.500 0.0720 0.01738 0.01080 0.0021 0.5286 0.9498
-1.250 0.1665 0.01722 0.01030 -0.0101 0.5170 0.9795
-1.000 0.2328 0.01660 0.00951 -0.0180 0.5067 0.9942
-0.750 0.2754 0.01620 0.00889 -0.0214 0.4999 0.9986
-0.500 0.3053 0.01602 0.00865 -0.0223 0.4932 1.0000
-0.250 0.3299 0.01595 0.00847 -0.0221 0.4874 1.0000
0.000 0.3545 0.01595 0.00832 -0.0219 0.4823 1.0000
0.250 0.3793 0.01589 0.00824 -0.0218 0.4761 1.0000
0.500 0.4041 0.01586 0.00813 -0.0216 0.4709 1.0000
0.750 0.4289 0.01593 0.00805 -0.0214 0.4667 1.0000
1.000 0.4540 0.01592 0.00807 -0.0212 0.4615 1.0000
1.250 0.4790 0.01594 0.00804 -0.0210 0.4564 1.0000
1.500 0.5039 0.01599 0.00799 -0.0208 0.4522 1.0000
1.750 0.5290 0.01608 0.00806 -0.0206 0.4478 1.0000
2.000 0.5541 0.01615 0.00814 -0.0205 0.4431 1.0000
2.250 0.5790 0.01621 0.00816 -0.0202 0.4388 1.0000
2.500 0.6040 0.01635 0.00819 -0.0200 0.4351 1.0000
2.750 0.6291 0.01647 0.00837 -0.0198 0.4308 1.0000
3.000 0.6541 0.01658 0.00851 -0.0196 0.4266 1.0000
3.250 0.6790 0.01670 0.00860 -0.0194 0.4227 1.0000
3.500 0.7040 0.01686 0.00868 -0.0191 0.4193 1.0000
3.750 0.7288 0.01705 0.00894 -0.0189 0.4152 1.0000
4.000 0.7536 0.01720 0.00916 -0.0187 0.4109 1.0000
4.250 0.7783 0.01734 0.00929 -0.0184 0.4070 1.0000
4.500 0.8032 0.01752 0.00940 -0.0181 0.4036 1.0000
4.750 0.8278 0.01778 0.00974 -0.0179 0.3999 1.0000
5.000 0.8520 0.01799 0.01005 -0.0176 0.3956 1.0000
5.250 0.8764 0.01815 0.01024 -0.0172 0.3916 1.0000
5.500 0.9012 0.01833 0.01038 -0.0169 0.3882 1.0000
5.750 0.9253 0.01864 0.01074 -0.0166 0.3845 1.0000
6.000 0.9488 0.01888 0.01112 -0.0162 0.3798 1.0000
6.250 0.9728 0.01907 0.01136 -0.0158 0.3758 1.0000
6.500 0.9974 0.01925 0.01151 -0.0154 0.3724 1.0000
6.750 1.0206 0.01958 0.01192 -0.0150 0.3682 1.0000
7.000 1.0431 0.01984 0.01233 -0.0144 0.3633 1.0000
7.250 1.0667 0.01998 0.01251 -0.0139 0.3590 1.0000
7.500 1.0916 0.02021 0.01266 -0.0136 0.3554 1.0000
7.750 1.1121 0.02056 0.01324 -0.0128 0.3503 1.0000
8.000 1.1341 0.02076 0.01355 -0.0121 0.3454 1.0000
8.250 1.1581 0.02086 0.01360 -0.0115 0.3412 1.0000
8.500 1.1787 0.02121 0.01410 -0.0107 0.3362 1.0000
8.750 1.1989 0.02143 0.01446 -0.0097 0.3306 1.0000
9.000 1.2221 0.02149 0.01449 -0.0091 0.3260 1.0000
9.250 1.2410 0.02181 0.01496 -0.0079 0.3204 1.0000
9.500 1.2602 0.02197 0.01525 -0.0067 0.3144 1.0000
9.750 1.2830 0.02203 0.01525 -0.0060 0.3094 1.0000
10.000 1.2979 0.02238 0.01585 -0.0043 0.3028 1.0000
10.250 1.3172 0.02243 0.01593 -0.0030 0.2968 1.0000
10.500 1.3336 0.02270 0.01632 -0.0015 0.2905 1.0000
10.750 1.3488 0.02288 0.01662 0.0003 0.2835 1.0000
11.000 1.3644 0.02309 0.01688 0.0021 0.2770 1.0000
11.250 1.3758 0.02335 0.01730 0.0044 0.2692 1.0000
11.500 1.3875 0.02364 0.01764 0.0067 0.2620 1.0000
11.750 1.3951 0.02398 0.01811 0.0096 0.2539 1.0000
12.000 1.4003 0.02442 0.01865 0.0128 0.2459 1.0000
12.250 1.4024 0.02485 0.01911 0.0165 0.2379 1.0000
12.500 1.3980 0.02546 0.01985 0.0211 0.2300 1.0000
12.750 1.3848 0.02598 0.02037 0.0271 0.2241 1.0000
13.000 1.3665 0.02668 0.02115 0.0336 0.2186 1.0000
13.250 1.3492 0.02761 0.02213 0.0390 0.2126 1.0000
13.500 1.3347 0.02883 0.02337 0.0432 0.2064 1.0000
13.750 1.3247 0.03059 0.02520 0.0454 0.1982 1.0000
14.000 1.3182 0.03287 0.02754 0.0461 0.1892 1.0000
14.250 1.3114 0.03557 0.03022 0.0461 0.1806 1.0000
14.500 1.3036 0.03876 0.03352 0.0454 0.1712 1.0000
14.750 1.2947 0.04221 0.03702 0.0446 0.1626 1.0000
15.000 1.2841 0.04585 0.04061 0.0437 0.1548 1.0000
15.250 1.2731 0.04982 0.04470 0.0425 0.1466 1.0000
15.500 1.2615 0.05372 0.04859 0.0415 0.1396 1.0000
15.750 1.2500 0.05789 0.05282 0.0402 0.1323 1.0000
16.000 1.2396 0.06198 0.05692 0.0389 0.1257 1.0000
16.250 1.2291 0.06626 0.06123 0.0375 0.1191 1.0000
16.500 1.2199 0.07040 0.06540 0.0361 0.1128 1.0000
16.750 1.2104 0.07476 0.06979 0.0345 0.1068 1.0000
17.000 1.2023 0.07885 0.07389 0.0331 0.1010 1.0000
17.250 1.1934 0.08328 0.07838 0.0314 0.0955 1.0000
17.500 1.1877 0.08710 0.08217 0.0301 0.0902 1.0000
17.750 1.1790 0.09168 0.08685 0.0282 0.0853 1.0000
18.000 1.1758 0.09508 0.09015 0.0271 0.0801 1.0000
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Polar data table (+)
Polar graphs
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