EPPLER 339 AIRFOIL (e339-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 339 AIRFOIL (e339-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.66 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e339-il-1000000.txt Download as CSV file: xf-e339-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 339 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3055 0.11278 0.11116 -0.0272 1.0000 0.0080
-10.500 -0.3028 0.10932 0.10772 -0.0282 1.0000 0.0080
-10.250 -0.3003 0.10587 0.10429 -0.0292 1.0000 0.0080
-10.000 -0.2857 0.10106 0.09948 -0.0340 0.9975 0.0080
-9.750 -0.2819 0.09693 0.09537 -0.0359 0.9828 0.0080
-9.500 -0.2280 0.08739 0.08573 -0.0544 0.9301 0.0081
-9.250 -0.1744 0.08112 0.07887 -0.0696 0.8117 0.0083
-9.000 -0.1747 0.07885 0.07641 -0.0694 0.7646 0.0084
-8.750 -0.1761 0.07583 0.07329 -0.0703 0.7366 0.0085
-8.500 -0.1793 0.07241 0.06980 -0.0718 0.7148 0.0085
-8.250 -0.1871 0.06863 0.06598 -0.0744 0.6971 0.0086
-8.000 -0.2000 0.06491 0.06220 -0.0756 0.6817 0.0085
-7.750 -0.2144 0.06189 0.05910 -0.0742 0.6680 0.0085
-7.500 -0.2182 0.05901 0.05614 -0.0736 0.6552 0.0086
-7.250 -0.2193 0.05594 0.05298 -0.0728 0.6436 0.0087
-7.000 -0.2178 0.05293 0.04985 -0.0719 0.6320 0.0088
-6.750 -0.2140 0.04987 0.04668 -0.0707 0.6217 0.0090
-6.500 -0.2078 0.04694 0.04361 -0.0694 0.6110 0.0090
-6.250 -0.2000 0.04396 0.04048 -0.0679 0.6010 0.0092
-6.000 -0.1910 0.04076 0.03710 -0.0660 0.5920 0.0097
-5.750 -0.1742 0.02086 0.01705 -0.0590 0.5733 0.0104
-5.500 -0.1715 0.01727 0.01324 -0.0566 0.5658 0.0106
-5.250 -0.1570 0.01553 0.01136 -0.0552 0.5576 0.0108
-5.000 -0.1405 0.01414 0.00983 -0.0540 0.5488 0.0110
-4.750 -0.1235 0.01253 0.00804 -0.0525 0.5412 0.0113
-4.500 -0.1114 0.00889 0.00382 -0.0489 0.5356 0.0133
-4.250 -0.0902 0.00835 0.00321 -0.0483 0.5264 0.0137
-4.000 -0.0707 0.00688 0.00127 -0.0462 0.5199 0.0161
-3.750 -0.0477 0.00629 0.00063 -0.0457 0.5118 0.0165
-3.500 -0.0239 0.00583 0.00009 -0.0452 0.5048 0.0173
-3.250 0.0036 0.01326 0.00665 -0.0448 0.5049 0.0113
-3.000 0.0297 0.01286 0.00616 -0.0443 0.4973 0.0119
-2.750 0.0552 0.01203 0.00519 -0.0435 0.4903 0.0115
-2.500 0.0803 0.01133 0.00436 -0.0426 0.4835 0.0107
-2.250 0.1052 0.01100 0.00394 -0.0419 0.4762 0.0106
-2.000 0.1301 0.01061 0.00352 -0.0412 0.4704 0.0106
-1.750 0.1549 0.01031 0.00317 -0.0405 0.4641 0.0106
-1.500 0.1791 0.01001 0.00282 -0.0396 0.4578 0.0109
-1.250 0.2050 0.00979 0.00259 -0.0391 0.4531 0.0114
-1.000 0.2309 0.00964 0.00241 -0.0387 0.4474 0.0120
-0.750 0.2563 0.00952 0.00222 -0.0381 0.4414 0.0140
-0.500 0.2821 0.00929 0.00206 -0.0375 0.4370 0.0307
-0.250 0.3071 0.00906 0.00200 -0.0370 0.4323 0.0875
0.000 0.3287 0.00856 0.00195 -0.0360 0.4277 0.2534
0.250 0.3246 0.00674 0.00207 -0.0298 0.4240 0.8656
0.500 0.3474 0.00698 0.00234 -0.0281 0.4206 0.8968
0.750 0.3677 0.00728 0.00265 -0.0258 0.4165 0.9146
1.000 0.3883 0.00751 0.00284 -0.0237 0.4123 0.9249
1.250 0.4110 0.00770 0.00297 -0.0223 0.4077 0.9312
1.500 0.4328 0.00781 0.00308 -0.0206 0.4051 0.9382
1.750 0.4543 0.00800 0.00325 -0.0187 0.4017 0.9468
2.000 0.4789 0.00805 0.00326 -0.0180 0.3979 0.9500
2.250 0.5052 0.00809 0.00324 -0.0177 0.3939 0.9508
2.500 0.5318 0.00813 0.00325 -0.0175 0.3904 0.9518
2.750 0.5592 0.00814 0.00324 -0.0175 0.3875 0.9527
3.000 0.5863 0.00817 0.00324 -0.0174 0.3842 0.9535
3.250 0.6129 0.00821 0.00326 -0.0173 0.3808 0.9544
3.500 0.6389 0.00829 0.00329 -0.0171 0.3771 0.9554
3.750 0.6651 0.00835 0.00333 -0.0169 0.3739 0.9566
4.000 0.6923 0.00837 0.00336 -0.0169 0.3713 0.9575
4.250 0.7192 0.00841 0.00339 -0.0168 0.3684 0.9583
4.500 0.7457 0.00847 0.00342 -0.0168 0.3649 0.9592
4.750 0.7717 0.00856 0.00349 -0.0166 0.3614 0.9601
5.000 0.7980 0.00866 0.00357 -0.0165 0.3581 0.9609
5.250 0.8252 0.00870 0.00362 -0.0166 0.3556 0.9617
5.500 0.8518 0.00873 0.00366 -0.0165 0.3527 0.9627
5.750 0.8781 0.00879 0.00373 -0.0164 0.3493 0.9636
6.000 0.9038 0.00890 0.00382 -0.0162 0.3455 0.9646
6.250 0.9297 0.00901 0.00393 -0.0161 0.3423 0.9655
6.500 0.9568 0.00905 0.00401 -0.0161 0.3394 0.9664
6.750 0.9833 0.00912 0.00409 -0.0161 0.3359 0.9675
7.000 1.0090 0.00922 0.00419 -0.0160 0.3322 0.9686
7.250 1.0331 0.00940 0.00434 -0.0155 0.3275 0.9699
7.500 1.0599 0.00944 0.00443 -0.0156 0.3246 0.9710
7.750 1.0857 0.00952 0.00453 -0.0155 0.3202 0.9723
8.000 1.1103 0.00964 0.00466 -0.0152 0.3161 0.9735
8.250 1.1354 0.00980 0.00482 -0.0150 0.3117 0.9750
8.500 1.1622 0.00987 0.00495 -0.0151 0.3079 0.9764
8.750 1.1883 0.01001 0.00510 -0.0152 0.3033 0.9779
9.000 1.2130 0.01021 0.00530 -0.0150 0.2980 0.9796
9.250 1.2397 0.01032 0.00546 -0.0152 0.2931 0.9811
9.500 1.2649 0.01050 0.00565 -0.0151 0.2870 0.9829
9.750 1.2903 0.01071 0.00587 -0.0152 0.2804 0.9847
10.000 1.3188 0.01093 0.00611 -0.0159 0.2731 0.9859
10.250 1.3465 0.01120 0.00639 -0.0165 0.2656 0.9871
10.500 1.3741 0.01148 0.00668 -0.0172 0.2574 0.9885
10.750 1.4008 0.01181 0.00701 -0.0177 0.2476 0.9901
11.000 1.4259 0.01220 0.00738 -0.0180 0.2373 0.9922
11.250 1.4498 0.01269 0.00783 -0.0182 0.2230 0.9948
11.500 1.4732 0.01322 0.00833 -0.0184 0.2096 0.9988
11.750 1.4758 0.01372 0.00876 -0.0145 0.1950 1.0000
12.000 1.4848 0.01432 0.00932 -0.0120 0.1822 1.0000
12.250 1.4916 0.01512 0.01005 -0.0093 0.1655 1.0000
12.500 1.4988 0.01593 0.01082 -0.0069 0.1531 1.0000
12.750 1.5052 0.01681 0.01167 -0.0046 0.1427 1.0000
13.000 1.5072 0.01794 0.01276 -0.0019 0.1301 1.0000
13.250 1.5110 0.01908 0.01390 0.0002 0.1223 1.0000
13.500 1.5083 0.02070 0.01548 0.0027 0.1105 1.0000
13.750 1.5119 0.02210 0.01692 0.0042 0.1044 1.0000
14.000 1.5066 0.02425 0.01905 0.0060 0.0943 1.0000
14.250 1.5022 0.02656 0.02136 0.0073 0.0869 1.0000
14.500 1.4988 0.02896 0.02379 0.0082 0.0805 1.0000
14.750 1.4968 0.03139 0.02626 0.0087 0.0764 1.0000
15.000 1.4892 0.03442 0.02932 0.0092 0.0706 1.0000
15.250 1.4829 0.03744 0.03239 0.0095 0.0658 1.0000
15.500 1.4792 0.04029 0.03532 0.0096 0.0638 1.0000
15.750 1.4690 0.04388 0.03894 0.0096 0.0599 1.0000
16.000 1.4589 0.04757 0.04269 0.0094 0.0558 1.0000
16.250 1.4500 0.05125 0.04643 0.0090 0.0536 1.0000
16.500 1.4420 0.05494 0.05018 0.0085 0.0505 1.0000
16.750 1.4319 0.05897 0.05427 0.0078 0.0478 1.0000
17.000 1.4193 0.06339 0.05872 0.0069 0.0434 1.0000
17.250 1.4115 0.06737 0.06276 0.0060 0.0416 1.0000
17.500 1.4023 0.07156 0.06702 0.0049 0.0394 1.0000
17.750 1.3943 0.07571 0.07123 0.0038 0.0371 1.0000
18.000 1.3844 0.08021 0.07577 0.0024 0.0348 1.0000
18.250 1.3787 0.08418 0.07981 0.0011 0.0325 1.0000
18.500 1.3702 0.08862 0.08428 -0.0004 0.0303 1.0000
18.750 1.3638 0.09286 0.08860 -0.0019 0.0288 1.0000
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Polar data table (+)
Polar graphs
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