GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Reynolds number: 50,000 Max Cl/Cd: 33.95 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe167-il-50000-n5.txt Download as CSV file: xf-goe167-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 167 (V.KARMAN PROP.2) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3458 0.10133 0.09505 -0.0250 1.0000 0.1063
-7.750 -0.3532 0.09963 0.09349 -0.0307 1.0000 0.1087
-7.500 -0.3493 0.09591 0.08986 -0.0335 1.0000 0.1099
-7.250 -0.3361 0.09163 0.08561 -0.0299 1.0000 0.1136
-7.000 -0.3315 0.08873 0.08280 -0.0317 1.0000 0.1194
-6.750 -0.3344 0.08672 0.08084 -0.0405 1.0000 0.1237
-6.500 -0.3252 0.08269 0.07693 -0.0339 1.0000 0.1292
-6.250 -0.3276 0.08109 0.07536 -0.0394 1.0000 0.1375
-5.750 -0.2791 0.07186 0.06608 -0.0480 0.9748 0.1550
-5.500 -0.2474 0.06751 0.06161 -0.0543 0.9557 0.1700
-5.250 -0.2198 0.06356 0.05763 -0.0569 0.9370 0.1881
-4.750 -0.1217 0.05100 0.04379 -0.0761 0.8968 0.0932
-4.500 -0.0815 0.04659 0.03865 -0.0807 0.8781 0.0809
-4.250 -0.0500 0.04340 0.03516 -0.0828 0.8603 0.0799
-4.000 -0.0177 0.04084 0.03205 -0.0846 0.8418 0.0808
-3.750 0.0118 0.03840 0.02923 -0.0856 0.8248 0.0801
-3.500 0.0409 0.03621 0.02665 -0.0863 0.8089 0.0788
-3.250 0.0701 0.03433 0.02433 -0.0867 0.7941 0.0778
-3.000 0.0993 0.03269 0.02225 -0.0870 0.7805 0.0771
-2.750 0.1284 0.03125 0.02038 -0.0870 0.7682 0.0768
-2.500 0.1572 0.03005 0.01877 -0.0870 0.7564 0.0772
-2.250 0.1862 0.02915 0.01746 -0.0870 0.7449 0.0799
-2.000 0.2150 0.02834 0.01628 -0.0869 0.7349 0.0818
-1.750 0.2429 0.02739 0.01511 -0.0867 0.7260 0.0826
-1.500 0.2705 0.02665 0.01421 -0.0865 0.7166 0.0835
-1.000 0.3260 0.02554 0.01277 -0.0859 0.7008 0.0867
-0.750 0.3538 0.02512 0.01216 -0.0855 0.6945 0.0892
-0.500 0.3814 0.02486 0.01178 -0.0855 0.6868 0.0923
-0.250 0.4091 0.02459 0.01137 -0.0854 0.6808 0.0980
0.000 0.4368 0.02446 0.01116 -0.0856 0.6742 0.1091
0.500 0.4940 0.02379 0.01070 -0.0862 0.6634 0.1636
1.000 0.5449 0.02220 0.01077 -0.0851 0.6522 1.0000
1.250 0.5726 0.02259 0.01092 -0.0852 0.6475 1.0000
1.500 0.5996 0.02309 0.01131 -0.0855 0.6417 1.0000
1.750 0.6270 0.02353 0.01159 -0.0856 0.6371 1.0000
2.000 0.6545 0.02395 0.01188 -0.0857 0.6331 1.0000
2.250 0.6806 0.02458 0.01250 -0.0860 0.6274 1.0000
2.500 0.7074 0.02508 0.01295 -0.0861 0.6227 1.0000
2.750 0.7348 0.02552 0.01331 -0.0861 0.6191 1.0000
3.000 0.7598 0.02630 0.01415 -0.0864 0.6137 1.0000
3.250 0.7856 0.02692 0.01479 -0.0865 0.6087 1.0000
3.500 0.8127 0.02736 0.01520 -0.0864 0.6046 1.0000
3.750 0.8364 0.02817 0.01612 -0.0864 0.5980 1.0000
4.000 0.8621 0.02864 0.01660 -0.0862 0.5916 1.0000
4.250 0.8866 0.02919 0.01720 -0.0858 0.5841 1.0000
4.500 0.9121 0.02950 0.01756 -0.0852 0.5758 1.0000
4.750 0.9353 0.03003 0.01818 -0.0847 0.5662 1.0000
5.000 0.9625 0.03016 0.01832 -0.0841 0.5590 1.0000
5.250 0.9837 0.03102 0.01938 -0.0837 0.5502 1.0000
5.500 1.0100 0.03140 0.01984 -0.0833 0.5444 1.0000
5.750 1.0309 0.03234 0.02099 -0.0829 0.5365 1.0000
6.000 1.0560 0.03281 0.02161 -0.0824 0.5300 1.0000
6.250 1.0767 0.03371 0.02272 -0.0819 0.5217 1.0000
6.500 1.1025 0.03395 0.02309 -0.0812 0.5139 1.0000
6.750 1.1215 0.03472 0.02407 -0.0803 0.5027 1.0000
7.000 1.1439 0.03499 0.02455 -0.0792 0.4915 1.0000
7.250 1.1698 0.03481 0.02449 -0.0782 0.4806 1.0000
7.500 1.1905 0.03508 0.02498 -0.0770 0.4680 1.0000
7.750 1.2079 0.03563 0.02578 -0.0756 0.4547 1.0000
8.000 1.2253 0.03609 0.02648 -0.0742 0.4410 1.0000
8.250 1.2415 0.03668 0.02738 -0.0727 0.4278 1.0000
8.500 1.2571 0.03742 0.02839 -0.0713 0.4158 1.0000
8.750 1.2719 0.03808 0.02933 -0.0697 0.4028 1.0000
9.000 1.2815 0.03886 0.03037 -0.0676 0.3856 1.0000
9.250 1.2930 0.03908 0.03074 -0.0652 0.3643 1.0000
9.500 1.2930 0.04038 0.03221 -0.0625 0.3385 1.0000
9.750 1.2928 0.04142 0.03329 -0.0595 0.3091 1.0000
10.000 1.2918 0.04276 0.03439 -0.0567 0.2723 1.0000
10.250 1.2839 0.04534 0.03667 -0.0546 0.2393 1.0000
10.500 1.2734 0.04889 0.04011 -0.0536 0.2121 1.0000
10.750 1.2633 0.05287 0.04412 -0.0532 0.1830 1.0000
11.000 1.2506 0.05730 0.04844 -0.0531 0.1396 1.0000
11.250 1.2335 0.06229 0.05306 -0.0532 0.1143 1.0000
11.500 1.2179 0.06727 0.05777 -0.0533 0.0997 1.0000
11.750 1.2046 0.07206 0.06242 -0.0535 0.0892 1.0000
12.000 1.1935 0.07667 0.06700 -0.0536 0.0811 1.0000
12.250 1.1822 0.08132 0.07162 -0.0538 0.0745 1.0000
12.500 1.1747 0.08557 0.07593 -0.0538 0.0680 1.0000
12.750 1.1682 0.08969 0.08010 -0.0538 0.0625 1.0000
13.000 1.1638 0.09346 0.08386 -0.0536 0.0580 1.0000
13.250 1.1652 0.09665 0.08724 -0.0532 0.0529 1.0000
13.500 1.1658 0.09989 0.09054 -0.0531 0.0489 1.0000
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Polar data table (+)
Polar graphs
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