GOE 399 AIRFOIL (goe399-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 399 AIRFOIL (goe399-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.41 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe399-il-1000000-n5.txt Download as CSV file: xf-goe399-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 399 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3756 0.09222 0.09063 -0.0268 1.0000 0.0037
-8.750 -0.3730 0.08948 0.08792 -0.0275 1.0000 0.0038
-7.750 -0.3943 0.01711 0.01369 -0.0919 0.9539 0.0048
-7.500 -0.3712 0.01502 0.01129 -0.0919 0.9455 0.0050
-7.250 -0.3460 0.01374 0.00977 -0.0918 0.9367 0.0052
-7.000 -0.3209 0.01284 0.00867 -0.0914 0.9251 0.0055
-6.750 -0.2961 0.01201 0.00763 -0.0910 0.9103 0.0058
-6.500 -0.2715 0.01124 0.00667 -0.0904 0.8924 0.0064
-6.250 -0.2466 0.01071 0.00597 -0.0898 0.8725 0.0069
-6.000 -0.2216 0.01029 0.00537 -0.0892 0.8522 0.0075
-5.750 -0.1965 0.00992 0.00481 -0.0886 0.8308 0.0080
-5.500 -0.1712 0.00958 0.00430 -0.0880 0.8114 0.0087
-5.250 -0.1457 0.00924 0.00384 -0.0874 0.7936 0.0103
-5.000 -0.1199 0.00900 0.00349 -0.0870 0.7774 0.0119
-4.750 -0.0937 0.00885 0.00330 -0.0866 0.7628 0.0152
-4.500 -0.0671 0.00881 0.00321 -0.0863 0.7490 0.0178
-4.250 -0.0404 0.00874 0.00304 -0.0859 0.7363 0.0188
-4.000 -0.0138 0.00860 0.00286 -0.0856 0.7261 0.0210
-3.750 0.0136 0.00860 0.00284 -0.0855 0.7180 0.0230
-3.500 0.0407 0.00853 0.00271 -0.0852 0.7104 0.0247
-3.250 0.0680 0.00847 0.00261 -0.0850 0.7028 0.0263
-3.000 0.0951 0.00845 0.00252 -0.0848 0.6948 0.0275
-2.750 0.1226 0.00845 0.00250 -0.0847 0.6865 0.0282
-2.500 0.1498 0.00842 0.00242 -0.0845 0.6793 0.0285
-2.250 0.1763 0.00813 0.00205 -0.0842 0.6720 0.0293
-2.000 0.2028 0.00790 0.00174 -0.0838 0.6649 0.0302
-1.750 0.2297 0.00774 0.00153 -0.0835 0.6564 0.0309
-1.500 0.2566 0.00763 0.00136 -0.0833 0.6480 0.0314
-1.250 0.2834 0.00754 0.00122 -0.0830 0.6389 0.0319
-1.000 0.3105 0.00746 0.00110 -0.0828 0.6293 0.0324
-0.750 0.3373 0.00742 0.00100 -0.0825 0.6164 0.0330
-0.500 0.3639 0.00740 0.00092 -0.0822 0.6007 0.0342
-0.250 0.3903 0.00742 0.00086 -0.0818 0.5819 0.0351
0.000 0.4167 0.00744 0.00081 -0.0815 0.5620 0.0366
0.250 0.4428 0.00751 0.00079 -0.0811 0.5374 0.0391
0.500 0.4687 0.00758 0.00080 -0.0807 0.5103 0.0505
0.750 0.4948 0.00765 0.00084 -0.0803 0.4882 0.0650
1.000 0.5211 0.00771 0.00087 -0.0800 0.4715 0.0756
1.250 0.5474 0.00780 0.00091 -0.0797 0.4548 0.0830
1.750 0.5991 0.00795 0.00105 -0.0790 0.4185 0.1398
2.000 0.6249 0.00785 0.00114 -0.0787 0.4090 0.2387
2.500 0.7063 0.00650 0.00146 -0.0854 0.3827 1.0000
2.750 0.7320 0.00663 0.00154 -0.0849 0.3730 1.0000
3.000 0.7571 0.00680 0.00164 -0.0844 0.3549 1.0000
3.250 0.7823 0.00698 0.00174 -0.0839 0.3379 1.0000
3.500 0.8071 0.00718 0.00186 -0.0833 0.3190 1.0000
3.750 0.8317 0.00741 0.00200 -0.0827 0.2956 1.0000
4.000 0.8554 0.00772 0.00218 -0.0820 0.2674 1.0000
4.250 0.8788 0.00806 0.00239 -0.0812 0.2384 1.0000
4.500 0.9023 0.00839 0.00262 -0.0805 0.2140 1.0000
4.750 0.9206 0.00924 0.00307 -0.0790 0.1318 1.0000
5.000 0.9392 0.01009 0.00359 -0.0775 0.0649 1.0000
5.250 0.9633 0.01037 0.00383 -0.0768 0.0554 1.0000
5.500 0.9875 0.01063 0.00409 -0.0762 0.0501 1.0000
5.750 1.0115 0.01090 0.00435 -0.0756 0.0442 1.0000
6.000 1.0360 0.01113 0.00459 -0.0750 0.0406 1.0000
6.250 1.0595 0.01145 0.00487 -0.0743 0.0343 1.0000
6.500 1.0811 0.01195 0.00525 -0.0733 0.0159 1.0000
6.750 1.1038 0.01234 0.00564 -0.0725 0.0112 1.0000
7.000 1.1270 0.01266 0.00600 -0.0717 0.0096 1.0000
7.250 1.1494 0.01305 0.00641 -0.0709 0.0082 1.0000
7.500 1.1709 0.01353 0.00693 -0.0699 0.0068 1.0000
7.750 1.1933 0.01390 0.00733 -0.0690 0.0063 1.0000
8.000 1.2151 0.01430 0.00777 -0.0681 0.0057 1.0000
8.250 1.2361 0.01476 0.00828 -0.0671 0.0051 1.0000
8.500 1.2556 0.01535 0.00891 -0.0658 0.0046 1.0000
8.750 1.2755 0.01587 0.00949 -0.0646 0.0044 1.0000
9.000 1.2953 0.01638 0.01006 -0.0634 0.0041 1.0000
9.250 1.3143 0.01692 0.01065 -0.0621 0.0038 1.0000
9.500 1.3320 0.01754 0.01135 -0.0606 0.0037 1.0000
9.750 1.3497 0.01812 0.01197 -0.0591 0.0034 1.0000
10.000 1.3659 0.01877 0.01268 -0.0574 0.0033 1.0000
10.250 1.3805 0.01949 0.01348 -0.0555 0.0030 1.0000
10.500 1.3875 0.02054 0.01463 -0.0523 0.0028 1.0000
10.750 1.3984 0.02123 0.01539 -0.0498 0.0028 1.0000
11.000 1.4097 0.02193 0.01617 -0.0475 0.0026 1.0000
11.250 1.4183 0.02282 0.01715 -0.0449 0.0026 1.0000
11.500 1.4265 0.02378 0.01821 -0.0424 0.0025 1.0000
11.750 1.4328 0.02492 0.01944 -0.0399 0.0024 1.0000
12.000 1.4423 0.02588 0.02048 -0.0380 0.0023 1.0000
12.250 1.4450 0.02742 0.02213 -0.0356 0.0023 1.0000
12.500 1.4509 0.02878 0.02360 -0.0337 0.0022 1.0000
12.750 1.4550 0.03038 0.02529 -0.0320 0.0021 1.0000
13.000 1.4587 0.03211 0.02713 -0.0305 0.0021 1.0000
13.250 1.4618 0.03398 0.02911 -0.0292 0.0021 1.0000
13.500 1.4623 0.03623 0.03150 -0.0280 0.0020 1.0000
13.750 1.4661 0.03825 0.03361 -0.0272 0.0019 1.0000
14.000 1.4661 0.04075 0.03623 -0.0266 0.0019 1.0000
14.250 1.4627 0.04375 0.03935 -0.0261 0.0019 1.0000
14.500 1.4656 0.04612 0.04181 -0.0259 0.0018 1.0000
14.750 1.4589 0.04976 0.04558 -0.0260 0.0018 1.0000
15.000 1.4510 0.05371 0.04968 -0.0263 0.0018 1.0000
15.250 1.4423 0.05797 0.05406 -0.0270 0.0017 1.0000
15.500 1.4309 0.06280 0.05903 -0.0282 0.0017 1.0000
15.750 1.4212 0.06767 0.06406 -0.0295 0.0017 1.0000
16.000 1.4099 0.07301 0.06954 -0.0314 0.0017 1.0000
16.250 1.3955 0.07908 0.07575 -0.0337 0.0017 1.0000
16.500 1.3782 0.08595 0.08278 -0.0366 0.0017 1.0000
17.000 1.3468 0.09975 0.09686 -0.0428 0.0016 1.0000
17.250 1.3388 0.10547 0.10269 -0.0455 0.0017 1.0000
17.500 1.3174 0.11408 0.11146 -0.0498 0.0017 1.0000
17.750 1.2966 0.12292 0.12044 -0.0545 0.0016 1.0000
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