GOE 673 AIRFOIL (goe673-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 673 AIRFOIL (goe673-il) Reynolds number: 500,000 Max Cl/Cd: 94.9 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe673-il-500000-n5.txt Download as CSV file: xf-goe673-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4457 0.08455 0.08240 -0.0426 1.0000 0.0046
-9.250 -0.4566 0.07840 0.07630 -0.0453 1.0000 0.0045
-9.000 -0.4827 0.07101 0.06903 -0.0473 1.0000 0.0043
-8.750 -0.4911 0.05112 0.04897 -0.0700 0.9892 0.0041
-8.500 -0.4913 0.04217 0.03961 -0.0785 0.9807 0.0040
-8.250 -0.4881 0.03453 0.03142 -0.0823 0.9725 0.0042
-8.000 -0.4690 0.03162 0.02822 -0.0841 0.9669 0.0044
-7.750 -0.4494 0.02970 0.02608 -0.0847 0.9593 0.0046
-7.500 -0.4274 0.02759 0.02370 -0.0853 0.9538 0.0049
-7.250 -0.4096 0.02442 0.02008 -0.0848 0.9465 0.0050
-7.000 -0.3886 0.02141 0.01662 -0.0844 0.9409 0.0050
-6.750 -0.3662 0.01924 0.01410 -0.0839 0.9348 0.0052
-6.500 -0.3422 0.01750 0.01207 -0.0834 0.9291 0.0054
-6.250 -0.3174 0.01609 0.01043 -0.0830 0.9239 0.0057
-6.000 -0.2924 0.01497 0.00912 -0.0826 0.9179 0.0060
-5.750 -0.2665 0.01409 0.00808 -0.0823 0.9128 0.0063
-5.500 -0.2415 0.01306 0.00692 -0.0821 0.9066 0.0068
-5.250 -0.2150 0.01262 0.00642 -0.0821 0.9007 0.0076
-5.000 -0.1883 0.01213 0.00586 -0.0820 0.8949 0.0084
-4.750 -0.1617 0.01154 0.00516 -0.0819 0.8884 0.0091
-4.500 -0.1346 0.01107 0.00459 -0.0818 0.8824 0.0099
-4.250 -0.1076 0.01049 0.00388 -0.0818 0.8755 0.0113
-4.000 -0.0801 0.01010 0.00340 -0.0818 0.8690 0.0142
-3.750 -0.0524 0.00982 0.00303 -0.0818 0.8615 0.0168
-3.500 -0.0245 0.00958 0.00270 -0.0819 0.8543 0.0228
-3.250 0.0026 0.00906 0.00236 -0.0820 0.8462 0.0787
-3.000 0.0296 0.00854 0.00212 -0.0823 0.8381 0.1665
-2.500 0.0841 0.00773 0.00182 -0.0827 0.8204 0.3336
-2.250 0.1117 0.00749 0.00172 -0.0829 0.8115 0.3929
-2.000 0.1396 0.00738 0.00163 -0.0830 0.8020 0.4272
-1.750 0.1677 0.00727 0.00156 -0.0832 0.7916 0.4604
-1.500 0.1957 0.00720 0.00149 -0.0833 0.7811 0.4869
-1.250 0.2236 0.00712 0.00143 -0.0834 0.7700 0.5140
-1.000 0.2514 0.00706 0.00138 -0.0835 0.7582 0.5417
-0.750 0.2791 0.00698 0.00136 -0.0836 0.7455 0.5757
-0.500 0.3065 0.00690 0.00136 -0.0836 0.7322 0.6231
-0.250 0.3338 0.00685 0.00138 -0.0835 0.7184 0.6672
0.000 0.3610 0.00683 0.00140 -0.0834 0.7041 0.7036
0.250 0.3881 0.00682 0.00142 -0.0833 0.6897 0.7336
0.500 0.4150 0.00683 0.00145 -0.0832 0.6751 0.7607
0.750 0.4414 0.00683 0.00150 -0.0829 0.6608 0.7923
1.000 0.4669 0.00681 0.00155 -0.0824 0.6467 0.8283
1.250 0.4903 0.00679 0.00163 -0.0813 0.6329 0.8752
1.500 0.5140 0.00681 0.00170 -0.0802 0.6190 0.9287
1.750 0.5440 0.00688 0.00174 -0.0807 0.6038 0.9667
2.250 0.6051 0.00713 0.00188 -0.0822 0.5730 1.0000
2.500 0.6322 0.00727 0.00198 -0.0822 0.5594 1.0000
2.750 0.6594 0.00741 0.00209 -0.0823 0.5459 1.0000
3.000 0.6866 0.00755 0.00223 -0.0823 0.5332 1.0000
3.250 0.7137 0.00770 0.00237 -0.0823 0.5198 1.0000
3.500 0.7406 0.00786 0.00252 -0.0823 0.5057 1.0000
3.750 0.7668 0.00808 0.00270 -0.0821 0.4855 1.0000
4.000 0.7907 0.00849 0.00291 -0.0816 0.4403 1.0000
4.250 0.8127 0.00907 0.00320 -0.0808 0.3768 1.0000
4.500 0.8326 0.00991 0.00361 -0.0798 0.2902 1.0000
4.750 0.8484 0.01121 0.00427 -0.0782 0.1666 1.0000
5.000 0.8609 0.01292 0.00527 -0.0761 0.0238 1.0000
5.250 0.8848 0.01339 0.00575 -0.0755 0.0142 1.0000
5.500 0.9092 0.01378 0.00619 -0.0751 0.0118 1.0000
5.750 0.9328 0.01424 0.00670 -0.0745 0.0098 1.0000
6.000 0.9540 0.01495 0.00751 -0.0734 0.0082 1.0000
6.250 0.9757 0.01558 0.00825 -0.0725 0.0076 1.0000
6.500 0.9978 0.01611 0.00884 -0.0717 0.0068 1.0000
6.750 1.0194 0.01666 0.00943 -0.0708 0.0060 1.0000
7.000 1.0393 0.01735 0.01017 -0.0697 0.0056 1.0000
7.250 1.0549 0.01839 0.01129 -0.0678 0.0052 1.0000
7.500 1.0702 0.01940 0.01241 -0.0659 0.0050 1.0000
7.750 1.0858 0.02037 0.01348 -0.0640 0.0047 1.0000
8.000 1.0997 0.02146 0.01468 -0.0619 0.0045 1.0000
8.250 1.1121 0.02265 0.01597 -0.0595 0.0043 1.0000
8.500 1.1237 0.02387 0.01731 -0.0570 0.0042 1.0000
8.750 1.1370 0.02499 0.01853 -0.0550 0.0039 1.0000
9.000 1.1511 0.02591 0.01957 -0.0532 0.0037 1.0000
9.250 1.1646 0.02683 0.02056 -0.0515 0.0035 1.0000
9.500 1.1764 0.02795 0.02175 -0.0496 0.0033 1.0000
9.750 1.1852 0.02999 0.02394 -0.0473 0.0031 1.0000
10.000 1.1964 0.03174 0.02591 -0.0453 0.0031 1.0000
10.250 1.2061 0.03387 0.02828 -0.0432 0.0030 1.0000
10.500 1.2131 0.03652 0.03123 -0.0407 0.0028 1.0000
10.750 1.2156 0.03978 0.03482 -0.0380 0.0027 1.0000
11.000 1.2121 0.04356 0.03894 -0.0349 0.0027 1.0000
11.250 1.2028 0.04781 0.04353 -0.0317 0.0026 1.0000
11.500 1.1904 0.05199 0.04801 -0.0290 0.0026 1.0000
11.750 1.1751 0.05649 0.05277 -0.0268 0.0026 1.0000
12.000 1.1576 0.06130 0.05783 -0.0254 0.0025 1.0000
12.250 1.1388 0.06648 0.06324 -0.0248 0.0025 1.0000
12.500 1.1192 0.07201 0.06897 -0.0252 0.0026 1.0000
12.750 1.0995 0.07795 0.07509 -0.0266 0.0026 1.0000
13.000 1.0792 0.08443 0.08174 -0.0290 0.0026 1.0000
13.250 1.0585 0.09156 0.08904 -0.0322 0.0026 1.0000
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Polar data table (+)
Polar graphs
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