GOE 673 AIRFOIL (goe673-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 673 AIRFOIL (goe673-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.51 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe673-il-1000000-n5.txt Download as CSV file: xf-goe673-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 673 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4727 0.08520 0.08369 -0.0410 1.0000 0.0025
-9.750 -0.4844 0.07828 0.07680 -0.0447 1.0000 0.0025
-9.250 -0.5246 0.04712 0.04548 -0.0766 0.9803 0.0024
-9.000 -0.5664 0.03010 0.02755 -0.0824 0.9599 0.0024
-8.750 -0.5719 0.02207 0.01860 -0.0814 0.9473 0.0025
-8.500 -0.5551 0.01957 0.01570 -0.0807 0.9389 0.0026
-8.250 -0.5334 0.01819 0.01411 -0.0803 0.9313 0.0027
-8.000 -0.5098 0.01726 0.01301 -0.0801 0.9255 0.0028
-7.750 -0.4850 0.01650 0.01213 -0.0800 0.9194 0.0029
-7.500 -0.4599 0.01588 0.01139 -0.0799 0.9136 0.0030
-7.250 -0.4348 0.01503 0.01039 -0.0798 0.9080 0.0032
-7.000 -0.4099 0.01404 0.00921 -0.0796 0.9020 0.0034
-6.750 -0.3848 0.01306 0.00804 -0.0793 0.8965 0.0036
-6.500 -0.3590 0.01227 0.00710 -0.0792 0.8905 0.0038
-6.250 -0.3327 0.01167 0.00637 -0.0791 0.8847 0.0040
-6.000 -0.3060 0.01107 0.00566 -0.0792 0.8787 0.0041
-5.750 -0.2795 0.01043 0.00491 -0.0791 0.8723 0.0045
-5.500 -0.2521 0.01008 0.00451 -0.0793 0.8662 0.0048
-5.250 -0.2246 0.00976 0.00412 -0.0794 0.8594 0.0052
-5.000 -0.1968 0.00947 0.00375 -0.0795 0.8530 0.0058
-4.750 -0.1689 0.00925 0.00347 -0.0796 0.8456 0.0063
-4.500 -0.1411 0.00887 0.00300 -0.0798 0.8382 0.0072
-4.250 -0.1132 0.00864 0.00271 -0.0799 0.8302 0.0082
-4.000 -0.0850 0.00844 0.00245 -0.0801 0.8217 0.0092
-3.750 -0.0569 0.00831 0.00225 -0.0803 0.8130 0.0102
-3.500 -0.0287 0.00810 0.00197 -0.0804 0.8035 0.0143
-3.250 -0.0003 0.00795 0.00179 -0.0806 0.7941 0.0183
-3.000 0.0275 0.00763 0.00157 -0.0809 0.7846 0.0618
-2.750 0.0551 0.00724 0.00139 -0.0812 0.7739 0.1357
-2.500 0.0833 0.00705 0.00127 -0.0814 0.7628 0.1724
-2.250 0.1112 0.00677 0.00116 -0.0818 0.7510 0.2372
-2.000 0.1389 0.00650 0.00109 -0.0821 0.7387 0.3144
-1.750 0.1671 0.00641 0.00103 -0.0823 0.7253 0.3487
-1.500 0.1953 0.00636 0.00098 -0.0825 0.7112 0.3751
-1.250 0.2233 0.00629 0.00096 -0.0827 0.6962 0.4102
-1.000 0.2514 0.00628 0.00094 -0.0830 0.6814 0.4371
-0.750 0.2796 0.00627 0.00093 -0.0832 0.6666 0.4611
-0.500 0.3077 0.00627 0.00093 -0.0834 0.6526 0.4838
-0.250 0.3358 0.00628 0.00094 -0.0836 0.6391 0.5047
0.000 0.3638 0.00627 0.00095 -0.0838 0.6257 0.5331
0.250 0.3918 0.00624 0.00098 -0.0840 0.6130 0.5695
0.500 0.4196 0.00619 0.00104 -0.0842 0.6001 0.6214
0.750 0.4474 0.00619 0.00110 -0.0844 0.5870 0.6606
1.000 0.4752 0.00622 0.00116 -0.0845 0.5721 0.6930
1.250 0.5028 0.00626 0.00122 -0.0846 0.5564 0.7193
1.500 0.5304 0.00631 0.00129 -0.0847 0.5415 0.7422
1.750 0.5580 0.00635 0.00137 -0.0848 0.5286 0.7675
2.000 0.5853 0.00637 0.00145 -0.0848 0.5160 0.7942
2.250 0.6124 0.00639 0.00154 -0.0847 0.5038 0.8225
2.500 0.6377 0.00638 0.00165 -0.0842 0.4906 0.8686
2.750 0.6596 0.00636 0.00175 -0.0828 0.4783 0.9353
3.000 0.6889 0.00640 0.00183 -0.0831 0.4665 0.9852
3.250 0.7184 0.00656 0.00193 -0.0837 0.4490 1.0000
3.500 0.7442 0.00687 0.00210 -0.0836 0.4145 1.0000
3.750 0.7676 0.00743 0.00236 -0.0831 0.3470 1.0000
4.000 0.7910 0.00801 0.00264 -0.0826 0.2848 1.0000
4.250 0.8111 0.00894 0.00310 -0.0816 0.1900 1.0000
4.500 0.8264 0.01042 0.00390 -0.0799 0.0414 1.0000
4.750 0.8507 0.01088 0.00424 -0.0795 0.0164 1.0000
5.000 0.8765 0.01117 0.00454 -0.0793 0.0111 1.0000
5.250 0.9017 0.01153 0.00491 -0.0789 0.0081 1.0000
5.500 0.9273 0.01182 0.00522 -0.0787 0.0073 1.0000
5.750 0.9524 0.01214 0.00556 -0.0784 0.0063 1.0000
6.000 0.9765 0.01257 0.00600 -0.0780 0.0052 1.0000
6.250 1.0008 0.01296 0.00645 -0.0775 0.0048 1.0000
6.500 1.0249 0.01335 0.00689 -0.0770 0.0044 1.0000
6.750 1.0484 0.01379 0.00736 -0.0765 0.0040 1.0000
7.000 1.0715 0.01424 0.00785 -0.0759 0.0037 1.0000
7.250 1.0935 0.01478 0.00842 -0.0751 0.0034 1.0000
7.500 1.1120 0.01562 0.00935 -0.0736 0.0031 1.0000
7.750 1.1333 0.01616 0.00995 -0.0727 0.0030 1.0000
8.000 1.1540 0.01672 0.01057 -0.0717 0.0028 1.0000
8.250 1.1737 0.01733 0.01125 -0.0706 0.0026 1.0000
8.500 1.1925 0.01800 0.01200 -0.0693 0.0024 1.0000
8.750 1.2098 0.01873 0.01281 -0.0678 0.0023 1.0000
9.000 1.2266 0.01946 0.01361 -0.0662 0.0022 1.0000
9.250 1.2416 0.02021 0.01442 -0.0644 0.0021 1.0000
9.500 1.2546 0.02096 0.01524 -0.0621 0.0021 1.0000
9.750 1.2664 0.02184 0.01619 -0.0598 0.0020 1.0000
10.000 1.2757 0.02294 0.01739 -0.0573 0.0019 1.0000
10.250 1.2798 0.02454 0.01914 -0.0541 0.0018 1.0000
10.500 1.2873 0.02596 0.02068 -0.0516 0.0018 1.0000
10.750 1.2964 0.02725 0.02210 -0.0494 0.0017 1.0000
11.000 1.3040 0.02872 0.02372 -0.0472 0.0017 1.0000
11.250 1.3114 0.03025 0.02538 -0.0451 0.0017 1.0000
11.500 1.3161 0.03212 0.02741 -0.0429 0.0016 1.0000
11.750 1.3195 0.03415 0.02965 -0.0407 0.0016 1.0000
12.000 1.3208 0.03650 0.03219 -0.0385 0.0015 1.0000
12.250 1.3190 0.03922 0.03513 -0.0362 0.0015 1.0000
12.500 1.3136 0.04244 0.03859 -0.0341 0.0014 1.0000
12.750 1.3030 0.04637 0.04278 -0.0320 0.0014 1.0000
13.000 1.2863 0.05122 0.04793 -0.0302 0.0013 1.0000
13.250 1.2567 0.05811 0.05518 -0.0288 0.0013 1.0000
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Polar data table (+)
Polar graphs
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