EPPLER 341 AIRFOIL (e341-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 341 AIRFOIL (e341-il) Reynolds number: 500,000 Max Cl/Cd: 85.25 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e341-il-500000.txt Download as CSV file: xf-e341-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4744 0.10130 0.09929 0.0001 1.0000 0.0166
-9.750 -0.4759 0.09630 0.09432 -0.0029 1.0000 0.0170
-9.500 -0.4796 0.09061 0.08866 -0.0070 1.0000 0.0174
-8.500 -0.4732 0.05219 0.04954 -0.0263 0.7714 0.0187
-8.250 -0.4831 0.04917 0.04636 -0.0241 0.7487 0.0188
-8.000 -0.5593 0.05633 0.05319 -0.0152 0.7838 0.0186
-7.750 -0.5546 0.05401 0.05070 -0.0137 0.7559 0.0188
-7.250 -0.5383 0.04962 0.04596 -0.0109 0.7119 0.0193
-7.000 -0.5282 0.04719 0.04333 -0.0093 0.6936 0.0198
-6.750 -0.5169 0.04454 0.04045 -0.0076 0.6774 0.0206
-6.500 -0.4759 0.02452 0.02010 -0.0080 0.6444 0.0232
-6.250 -0.4613 0.02266 0.01814 -0.0069 0.6313 0.0236
-6.000 -0.4463 0.02077 0.01610 -0.0055 0.6187 0.0243
-5.750 -0.4311 0.01867 0.01378 -0.0037 0.6075 0.0255
-4.500 -0.3517 0.01830 0.01080 0.0101 0.5704 0.0144
-4.250 -0.3238 0.01690 0.00925 0.0103 0.5600 0.0140
-4.000 -0.2965 0.01587 0.00806 0.0108 0.5498 0.0138
-3.750 -0.2700 0.01503 0.00712 0.0113 0.5400 0.0137
-3.500 -0.2447 0.01438 0.00636 0.0119 0.5307 0.0139
-3.250 -0.2198 0.01382 0.00574 0.0127 0.5212 0.0143
-3.000 -0.1950 0.01341 0.00524 0.0134 0.5125 0.0147
-2.750 -0.1719 0.01282 0.00463 0.0144 0.5041 0.0160
-2.500 -0.1468 0.01253 0.00428 0.0151 0.4965 0.0176
-2.250 -0.1220 0.01218 0.00391 0.0158 0.4887 0.0208
-2.000 -0.0975 0.01187 0.00358 0.0166 0.4818 0.0306
-1.750 -0.0758 0.01125 0.00330 0.0177 0.4747 0.1061
-1.500 -0.0591 0.01038 0.00306 0.0195 0.4684 0.2835
-1.250 -0.0749 0.00806 0.00269 0.0279 0.4646 0.7529
-1.000 -0.0490 0.00898 0.00392 0.0303 0.4578 0.8838
-0.750 -0.0211 0.01011 0.00494 0.0319 0.4518 0.9082
-0.500 0.0403 0.01121 0.00594 0.0265 0.4443 0.9156
-0.250 0.0951 0.01190 0.00648 0.0219 0.4372 0.9254
0.000 0.1540 0.01245 0.00690 0.0163 0.4303 0.9330
0.250 0.1937 0.01267 0.00704 0.0142 0.4245 0.9404
0.500 0.2293 0.01271 0.00696 0.0125 0.4195 0.9424
0.750 0.2610 0.01269 0.00690 0.0116 0.4150 0.9445
1.000 0.2890 0.01269 0.00685 0.0115 0.4104 0.9474
1.250 0.3085 0.01275 0.00685 0.0131 0.4063 0.9516
1.500 0.3430 0.01274 0.00675 0.0115 0.4018 0.9526
1.750 0.3765 0.01267 0.00666 0.0102 0.3979 0.9538
2.000 0.4088 0.01264 0.00660 0.0092 0.3938 0.9552
2.250 0.4389 0.01265 0.00655 0.0085 0.3897 0.9569
2.500 0.4667 0.01273 0.00656 0.0083 0.3860 0.9589
2.750 0.4859 0.01279 0.00664 0.0099 0.3832 0.9621
3.000 0.5174 0.01273 0.00657 0.0090 0.3796 0.9632
3.250 0.5501 0.01270 0.00651 0.0077 0.3758 0.9641
3.500 0.5807 0.01274 0.00650 0.0069 0.3721 0.9650
3.750 0.6108 0.01277 0.00652 0.0062 0.3688 0.9661
4.000 0.6403 0.01276 0.00654 0.0056 0.3654 0.9675
4.250 0.6675 0.01278 0.00657 0.0055 0.3620 0.9688
4.500 0.6929 0.01284 0.00661 0.0058 0.3590 0.9702
4.750 0.7129 0.01304 0.00676 0.0071 0.3557 0.9723
5.000 0.7435 0.01301 0.00677 0.0062 0.3526 0.9728
5.250 0.7731 0.01300 0.00681 0.0056 0.3491 0.9734
5.500 0.8026 0.01301 0.00683 0.0049 0.3456 0.9741
5.750 0.8322 0.01308 0.00689 0.0043 0.3422 0.9750
6.000 0.8601 0.01323 0.00702 0.0039 0.3388 0.9758
6.250 0.8866 0.01324 0.00711 0.0039 0.3354 0.9765
6.500 0.9124 0.01328 0.00720 0.0040 0.3318 0.9772
6.750 0.9381 0.01335 0.00728 0.0041 0.3281 0.9782
7.000 0.9627 0.01357 0.00745 0.0044 0.3241 0.9793
7.250 0.9857 0.01361 0.00759 0.0050 0.3211 0.9800
7.500 1.0071 0.01368 0.00773 0.0060 0.3172 0.9808
7.750 1.0339 0.01373 0.00781 0.0058 0.3130 0.9813
8.000 1.0623 0.01391 0.00797 0.0053 0.3086 0.9820
8.250 1.0895 0.01392 0.00810 0.0050 0.3044 0.9826
8.500 1.1148 0.01398 0.00821 0.0051 0.2996 0.9830
8.750 1.1388 0.01415 0.00837 0.0054 0.2946 0.9836
9.000 1.1633 0.01423 0.00856 0.0056 0.2899 0.9841
9.250 1.1871 0.01433 0.00872 0.0060 0.2845 0.9847
9.500 1.2102 0.01454 0.00892 0.0064 0.2788 0.9856
9.750 1.2340 0.01463 0.00914 0.0068 0.2729 0.9865
10.000 1.2541 0.01483 0.00936 0.0078 0.2667 0.9872
10.250 1.2737 0.01501 0.00961 0.0089 0.2599 0.9880
10.500 1.2940 0.01525 0.00987 0.0098 0.2526 0.9887
10.750 1.3180 0.01546 0.01016 0.0099 0.2442 0.9892
11.000 1.3399 0.01578 0.01049 0.0103 0.2346 0.9899
11.250 1.3610 0.01614 0.01088 0.0107 0.2241 0.9907
11.500 1.3826 0.01656 0.01133 0.0110 0.2125 0.9919
11.750 1.3998 0.01707 0.01186 0.0121 0.2006 0.9930
12.000 1.4135 0.01768 0.01247 0.0136 0.1883 0.9943
12.250 1.4270 0.01839 0.01317 0.0150 0.1758 0.9955
12.500 1.4416 0.01924 0.01401 0.0159 0.1619 0.9967
12.750 1.4517 0.02021 0.01498 0.0172 0.1490 0.9983
13.000 1.4480 0.02121 0.01599 0.0209 0.1399 1.0000
13.250 1.4286 0.02210 0.01694 0.0274 0.1351 1.0000
13.500 1.4057 0.02340 0.01828 0.0333 0.1309 1.0000
13.750 1.3835 0.02496 0.01990 0.0384 0.1272 1.0000
14.000 1.3686 0.02682 0.02181 0.0416 0.1218 1.0000
14.250 1.3611 0.02970 0.02473 0.0417 0.1147 1.0000
14.500 1.3569 0.03286 0.02793 0.0407 0.1070 1.0000
14.750 1.3503 0.03646 0.03159 0.0395 0.1004 1.0000
15.000 1.3406 0.04047 0.03564 0.0382 0.0943 1.0000
15.250 1.3309 0.04448 0.03971 0.0369 0.0891 1.0000
15.500 1.3193 0.04872 0.04401 0.0356 0.0842 1.0000
15.750 1.3046 0.05331 0.04865 0.0343 0.0801 1.0000
16.000 1.2955 0.05739 0.05280 0.0330 0.0758 1.0000
16.250 1.2817 0.06212 0.05757 0.0315 0.0720 1.0000
16.500 1.2711 0.06657 0.06209 0.0300 0.0684 1.0000
16.750 1.2620 0.07088 0.06646 0.0285 0.0647 1.0000
17.000 1.2491 0.07574 0.07135 0.0268 0.0613 1.0000
17.250 1.2415 0.07997 0.07564 0.0253 0.0581 1.0000
17.500 1.2331 0.08433 0.08006 0.0238 0.0548 1.0000
17.750 1.2210 0.08925 0.08502 0.0220 0.0519 1.0000
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