GOE 14K AIRFOIL (goe14k-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 14K AIRFOIL (goe14k-il) Reynolds number: 500,000 Max Cl/Cd: 76.8 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe14k-il-500000-n5.txt Download as CSV file: xf-goe14k-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 14K 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.6106 0.09383 0.09120 -0.0825 0.9836 0.0071
-14.250 -0.6734 0.07772 0.07497 -0.0909 0.9819 0.0069
-14.000 -0.7592 0.05500 0.05192 -0.1070 0.9797 0.0065
-13.750 -0.7892 0.04347 0.04000 -0.1192 0.9780 0.0064
-13.500 -0.7974 0.04080 0.03723 -0.1183 0.9736 0.0066
-13.250 -0.8083 0.03748 0.03369 -0.1178 0.9706 0.0065
-13.000 -0.8012 0.03572 0.03179 -0.1175 0.9690 0.0069
-12.750 -0.8158 0.03318 0.02902 -0.1134 0.9647 0.0067
-12.500 -0.8134 0.03190 0.02758 -0.1106 0.9606 0.0070
-12.250 -0.8080 0.03029 0.02578 -0.1086 0.9582 0.0071
-12.000 -0.7999 0.02865 0.02394 -0.1068 0.9566 0.0072
-11.750 -0.8043 0.02788 0.02301 -0.1012 0.9493 0.0076
-11.500 -0.7948 0.02673 0.02169 -0.0988 0.9464 0.0077
-11.250 -0.7835 0.02545 0.02023 -0.0967 0.9445 0.0079
-11.000 -0.7888 0.02462 0.01930 -0.0907 0.9376 0.0080
-10.750 -0.7775 0.02375 0.01832 -0.0881 0.9343 0.0082
-10.500 -0.7609 0.02281 0.01727 -0.0867 0.9324 0.0086
-10.250 -0.7410 0.02197 0.01632 -0.0858 0.9310 0.0089
-10.000 -0.7299 0.02122 0.01544 -0.0828 0.9271 0.0091
-9.750 -0.7192 0.02052 0.01461 -0.0796 0.9224 0.0096
-9.500 -0.7008 0.01976 0.01371 -0.0782 0.9201 0.0098
-9.250 -0.6799 0.01896 0.01280 -0.0772 0.9184 0.0105
-9.000 -0.6570 0.01822 0.01197 -0.0767 0.9171 0.0108
-8.750 -0.6317 0.01757 0.01124 -0.0766 0.9161 0.0114
-8.500 -0.6176 0.01716 0.01074 -0.0739 0.9118 0.0121
-8.250 -0.5986 0.01669 0.01017 -0.0723 0.9085 0.0128
-8.000 -0.5764 0.01608 0.00949 -0.0715 0.9064 0.0138
-7.750 -0.5511 0.01555 0.00889 -0.0713 0.9049 0.0147
-7.500 -0.5236 0.01506 0.00832 -0.0716 0.9037 0.0159
-7.250 -0.4951 0.01451 0.00772 -0.0721 0.9027 0.0179
-7.000 -0.4652 0.01403 0.00718 -0.0729 0.9019 0.0199
-6.750 -0.4343 0.01359 0.00668 -0.0739 0.9011 0.0227
-6.500 -0.4236 0.01340 0.00651 -0.0703 0.8959 0.0264
-6.250 -0.3996 0.01311 0.00623 -0.0697 0.8933 0.0317
-6.000 -0.3718 0.01287 0.00598 -0.0699 0.8914 0.0380
-5.750 -0.3416 0.01269 0.00574 -0.0707 0.8900 0.0419
-5.500 -0.3104 0.01238 0.00542 -0.0718 0.8888 0.0465
-5.250 -0.2778 0.01216 0.00516 -0.0731 0.8878 0.0508
-5.000 -0.2441 0.01196 0.00490 -0.0747 0.8870 0.0540
-4.750 -0.2097 0.01177 0.00466 -0.0764 0.8862 0.0559
-4.500 -0.2045 0.01168 0.00456 -0.0715 0.8811 0.0584
-4.250 -0.1809 0.01149 0.00436 -0.0707 0.8787 0.0623
-4.000 -0.1536 0.01132 0.00416 -0.0708 0.8768 0.0655
-3.750 -0.1242 0.01116 0.00395 -0.0714 0.8754 0.0674
-3.500 -0.0928 0.01093 0.00371 -0.0724 0.8742 0.0706
-3.250 -0.0601 0.01073 0.00351 -0.0738 0.8732 0.0749
-3.000 -0.0259 0.01054 0.00331 -0.0755 0.8722 0.0809
-2.750 0.0093 0.01025 0.00312 -0.0775 0.8713 0.1048
-2.500 0.0147 0.01013 0.00317 -0.0726 0.8670 0.1465
-2.250 0.0366 0.00995 0.00311 -0.0715 0.8647 0.1863
-2.000 0.0631 0.00975 0.00305 -0.0715 0.8629 0.2233
-1.750 0.0926 0.00952 0.00298 -0.0723 0.8615 0.2723
-1.500 0.1227 0.00934 0.00293 -0.0731 0.8602 0.3105
-1.250 0.1539 0.00908 0.00287 -0.0743 0.8590 0.3708
-1.000 0.1864 0.00884 0.00281 -0.0756 0.8580 0.4249
-0.750 0.2186 0.00848 0.00274 -0.0770 0.8569 0.5053
-0.500 0.3150 0.00754 0.00314 -0.0935 0.8588 0.8532
-0.250 0.4025 0.00799 0.00367 -0.1071 0.8593 0.8902
0.000 0.4483 0.00817 0.00383 -0.1112 0.8574 0.9053
0.250 0.4757 0.00838 0.00404 -0.1110 0.8547 0.9210
0.750 0.5264 0.00893 0.00463 -0.1096 0.8469 0.9470
1.000 0.5681 0.00897 0.00462 -0.1128 0.8414 0.9513
1.500 0.6233 0.00916 0.00480 -0.1126 0.8248 0.9595
1.750 0.6343 0.00933 0.00499 -0.1087 0.8156 0.9660
2.000 0.6691 0.00935 0.00501 -0.1104 0.8063 0.9678
2.250 0.6958 0.00939 0.00503 -0.1101 0.7907 0.9711
2.500 0.7089 0.00957 0.00517 -0.1067 0.7708 0.9765
2.750 0.7373 0.00960 0.00512 -0.1068 0.7367 0.9790
3.000 0.7445 0.01003 0.00520 -0.1021 0.6561 0.9846
3.250 0.7464 0.01071 0.00547 -0.0966 0.5740 0.9887
3.500 0.7376 0.01186 0.00600 -0.0891 0.4455 0.9934
3.750 0.7522 0.01240 0.00630 -0.0867 0.3935 0.9956
4.000 0.7714 0.01274 0.00649 -0.0853 0.3535 0.9972
4.250 0.7870 0.01330 0.00676 -0.0834 0.2857 0.9989
4.500 0.8023 0.01385 0.00705 -0.0813 0.2289 1.0000
4.750 0.8106 0.01435 0.00738 -0.0776 0.1889 1.0000
5.000 0.8193 0.01491 0.00773 -0.0740 0.1473 1.0000
5.250 0.8298 0.01542 0.00806 -0.0707 0.1100 1.0000
5.500 0.8438 0.01576 0.00834 -0.0682 0.0959 1.0000
5.750 0.8576 0.01613 0.00867 -0.0656 0.0829 1.0000
6.000 0.8722 0.01648 0.00898 -0.0632 0.0732 1.0000
6.250 0.8874 0.01683 0.00931 -0.0610 0.0662 1.0000
6.500 0.9031 0.01715 0.00965 -0.0588 0.0610 1.0000
6.750 0.9185 0.01749 0.00999 -0.0566 0.0553 1.0000
7.000 0.9340 0.01784 0.01035 -0.0545 0.0484 1.0000
7.250 0.9489 0.01825 0.01072 -0.0522 0.0375 1.0000
7.500 0.9638 0.01868 0.01112 -0.0500 0.0300 1.0000
7.750 0.9779 0.01917 0.01159 -0.0477 0.0246 1.0000
8.000 0.9924 0.01964 0.01209 -0.0454 0.0208 1.0000
8.250 1.0067 0.02015 0.01260 -0.0432 0.0186 1.0000
8.500 1.0212 0.02067 0.01316 -0.0410 0.0167 1.0000
8.750 1.0357 0.02119 0.01373 -0.0388 0.0153 1.0000
9.000 1.0493 0.02179 0.01433 -0.0366 0.0134 1.0000
9.250 1.0633 0.02235 0.01497 -0.0345 0.0134 1.0000
9.500 1.0778 0.02289 0.01556 -0.0324 0.0125 1.0000
9.750 1.0915 0.02350 0.01621 -0.0303 0.0114 1.0000
10.000 1.1040 0.02421 0.01695 -0.0280 0.0106 1.0000
10.250 1.1169 0.02487 0.01770 -0.0258 0.0104 1.0000
10.500 1.1288 0.02564 0.01855 -0.0235 0.0100 1.0000
10.750 1.1419 0.02631 0.01928 -0.0214 0.0093 1.0000
11.000 1.1532 0.02711 0.02016 -0.0191 0.0092 1.0000
11.250 1.1659 0.02781 0.02091 -0.0171 0.0087 1.0000
11.500 1.1749 0.02881 0.02197 -0.0146 0.0084 1.0000
11.750 1.1833 0.02985 0.02311 -0.0121 0.0081 1.0000
12.000 1.1934 0.03077 0.02413 -0.0098 0.0079 1.0000
12.250 1.2028 0.03176 0.02521 -0.0076 0.0075 1.0000
12.500 1.2107 0.03287 0.02641 -0.0052 0.0072 1.0000
12.750 1.2191 0.03394 0.02760 -0.0029 0.0070 1.0000
13.000 1.2248 0.03524 0.02900 -0.0005 0.0069 1.0000
13.250 1.2311 0.03649 0.03034 0.0018 0.0067 1.0000
13.500 1.2358 0.03791 0.03188 0.0042 0.0068 1.0000
13.750 1.2399 0.03938 0.03342 0.0065 0.0066 1.0000
14.000 1.2403 0.04117 0.03529 0.0090 0.0063 1.0000
14.250 1.2446 0.04271 0.03701 0.0110 0.0061 1.0000
14.500 1.2410 0.04501 0.03943 0.0137 0.0062 1.0000
14.750 1.2443 0.04674 0.04133 0.0155 0.0058 1.0000
15.000 1.2468 0.04853 0.04325 0.0172 0.0056 1.0000
15.250 1.2423 0.05107 0.04593 0.0192 0.0057 1.0000
15.500 1.2369 0.05384 0.04886 0.0211 0.0057 1.0000
15.750 1.2329 0.05655 0.05172 0.0224 0.0055 1.0000
16.000 1.2307 0.05916 0.05443 0.0234 0.0052 1.0000
16.250 1.2213 0.06277 0.05822 0.0243 0.0053 1.0000
16.500 1.2117 0.06663 0.06222 0.0247 0.0052 1.0000
16.750 1.1996 0.07107 0.06683 0.0247 0.0052 1.0000
17.000 1.1738 0.07783 0.07384 0.0238 0.0054 1.0000
17.250 1.1771 0.08054 0.07660 0.0230 0.0052 1.0000
17.500 1.1570 0.08721 0.08347 0.0208 0.0052 1.0000
17.750 1.1527 0.09161 0.08792 0.0188 0.0049 1.0000
18.000 1.1187 0.10169 0.09829 0.0145 0.0052 1.0000
18.250 1.0964 0.11007 0.10683 0.0104 0.0051 1.0000
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Polar data table (+)
Polar graphs
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