GOE 379 AIRFOIL (goe379-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 379 AIRFOIL (goe379-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.34 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe379-il-1000000.txt Download as CSV file: xf-goe379-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 379 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2285 0.08556 0.08413 -0.0280 1.0000 0.0071
-8.250 -0.2275 0.08254 0.08113 -0.0282 1.0000 0.0072
-8.000 -0.2277 0.07964 0.07825 -0.0281 1.0000 0.0072
-7.750 -0.2215 0.07600 0.07462 -0.0299 0.9986 0.0072
-6.500 -0.2307 0.06965 0.06819 -0.0473 0.9744 0.0076
-6.250 -0.2004 0.06600 0.06451 -0.0534 0.9693 0.0079
-6.000 -0.1653 0.06180 0.06026 -0.0612 0.9586 0.0083
-5.750 -0.1277 0.05762 0.05600 -0.0692 0.9429 0.0091
-5.500 -0.0985 0.05387 0.05212 -0.0745 0.9168 0.0100
-5.250 -0.0751 0.05073 0.04882 -0.0773 0.8908 0.0109
-5.000 -0.0528 0.04795 0.04588 -0.0791 0.8696 0.0112
-4.750 -0.0318 0.04497 0.04276 -0.0804 0.8509 0.0113
-4.500 -0.0104 0.04190 0.03956 -0.0815 0.8361 0.0113
-4.250 0.0118 0.03869 0.03619 -0.0824 0.8225 0.0114
-4.000 0.0343 0.03549 0.03284 -0.0830 0.8099 0.0114
-3.250 0.0981 0.02279 0.01937 -0.0823 0.7756 0.0103
-3.000 0.1120 0.01256 0.00807 -0.0783 0.7674 0.0103
-2.750 0.1362 0.01119 0.00637 -0.0774 0.7566 0.0107
-2.500 0.1611 0.01014 0.00504 -0.0765 0.7450 0.0111
-2.250 0.1862 0.00933 0.00399 -0.0758 0.7328 0.0119
-2.000 0.2106 0.00833 0.00274 -0.0748 0.7201 0.0131
-1.750 0.2364 0.00801 0.00232 -0.0742 0.7069 0.0148
-1.500 0.2622 0.00779 0.00200 -0.0736 0.6936 0.0165
-1.250 0.2878 0.00755 0.00165 -0.0729 0.6798 0.0184
-1.000 0.3134 0.00739 0.00144 -0.0723 0.6649 0.0254
-0.750 0.3396 0.00738 0.00139 -0.0719 0.6487 0.0367
-0.500 0.3656 0.00735 0.00132 -0.0714 0.6316 0.0456
-0.250 0.3921 0.00745 0.00136 -0.0711 0.6146 0.0492
0.000 0.4175 0.00738 0.00120 -0.0706 0.5973 0.0548
0.250 0.4433 0.00742 0.00117 -0.0701 0.5798 0.0597
0.500 0.4695 0.00748 0.00116 -0.0697 0.5632 0.0629
0.750 0.4949 0.00744 0.00107 -0.0692 0.5470 0.0710
1.000 0.5210 0.00749 0.00105 -0.0688 0.5324 0.0764
1.250 0.5468 0.00749 0.00104 -0.0684 0.5195 0.0899
1.500 0.5726 0.00749 0.00105 -0.0680 0.5078 0.1139
1.750 0.5975 0.00739 0.00112 -0.0674 0.4953 0.2087
2.000 0.7027 0.00597 0.00137 -0.0860 0.4704 1.0000
2.250 0.7279 0.00609 0.00141 -0.0854 0.4572 1.0000
2.500 0.7530 0.00621 0.00146 -0.0848 0.4433 1.0000
2.750 0.7778 0.00635 0.00152 -0.0842 0.4285 1.0000
3.250 0.8273 0.00665 0.00170 -0.0831 0.3999 1.0000
3.500 0.8521 0.00679 0.00180 -0.0825 0.3873 1.0000
3.750 0.8768 0.00694 0.00190 -0.0819 0.3756 1.0000
4.250 0.9249 0.00735 0.00217 -0.0805 0.3428 1.0000
4.500 0.9490 0.00755 0.00233 -0.0798 0.3297 1.0000
4.750 0.9730 0.00775 0.00248 -0.0792 0.3159 1.0000
5.000 0.9968 0.00796 0.00264 -0.0785 0.2991 1.0000
5.250 1.0201 0.00822 0.00283 -0.0777 0.2790 1.0000
5.500 1.0411 0.00868 0.00309 -0.0766 0.2366 1.0000
5.750 1.0540 0.00988 0.00374 -0.0742 0.1428 1.0000
6.000 1.0611 0.01171 0.00491 -0.0707 0.0156 1.0000
6.250 1.0836 0.01203 0.00529 -0.0697 0.0140 1.0000
6.500 1.1051 0.01243 0.00575 -0.0686 0.0120 1.0000
6.750 1.1243 0.01307 0.00648 -0.0670 0.0097 1.0000
7.000 1.1422 0.01381 0.00736 -0.0652 0.0088 1.0000
7.250 1.1623 0.01429 0.00791 -0.0639 0.0085 1.0000
7.500 1.1818 0.01481 0.00849 -0.0624 0.0079 1.0000
7.750 1.1995 0.01547 0.00922 -0.0607 0.0073 1.0000
8.000 1.2154 0.01624 0.01007 -0.0587 0.0068 1.0000
8.250 1.2310 0.01699 0.01088 -0.0567 0.0064 1.0000
8.500 1.2451 0.01780 0.01175 -0.0546 0.0059 1.0000
8.750 1.2479 0.01940 0.01347 -0.0506 0.0054 1.0000
9.000 1.2502 0.02103 0.01520 -0.0466 0.0053 1.0000
9.250 1.2498 0.02285 0.01711 -0.0422 0.0052 1.0000
9.500 1.2542 0.02479 0.01912 -0.0388 0.0052 1.0000
9.750 1.2701 0.02440 0.01882 -0.0370 0.0049 1.0000
10.000 1.2760 0.02607 0.02059 -0.0340 0.0049 1.0000
10.250 1.2884 0.02655 0.02115 -0.0321 0.0045 1.0000
10.500 1.2956 0.02813 0.02284 -0.0297 0.0043 1.0000
10.750 1.3030 0.02994 0.02477 -0.0274 0.0041 1.0000
11.000 1.3106 0.03203 0.02700 -0.0252 0.0041 1.0000
11.250 1.3177 0.03471 0.02986 -0.0229 0.0040 1.0000
11.500 1.3212 0.03908 0.03455 -0.0204 0.0044 1.0000
14.750 1.0348 0.09537 0.09304 -0.0164 0.0058 1.0000
15.000 1.0056 0.10292 0.10076 -0.0210 0.0059 1.0000
15.250 0.9730 0.11051 0.10852 -0.0263 0.0060 1.0000
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Polar data table (+)
Polar graphs
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