GOE 177 AIRFOIL (goe177-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 177 AIRFOIL (goe177-il) Reynolds number: 50,000 Max Cl/Cd: 41.5 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe177-il-50000-n5.txt Download as CSV file: xf-goe177-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 177 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3052 0.10234 0.09611 -0.0216 1.0000 0.0768
-7.250 -0.3059 0.10043 0.09432 -0.0227 1.0000 0.0787
-7.000 -0.3058 0.09880 0.09281 -0.0257 1.0000 0.0801
-6.750 -0.3027 0.09689 0.09101 -0.0294 1.0000 0.0807
-6.500 -0.2970 0.09458 0.08878 -0.0330 1.0000 0.0810
-6.250 -0.2912 0.09030 0.08460 -0.0317 1.0000 0.0818
-6.000 -0.2854 0.08628 0.08065 -0.0285 1.0000 0.0838
-5.750 -0.2795 0.08333 0.07777 -0.0288 1.0000 0.0849
-5.500 -0.2731 0.08044 0.07492 -0.0299 1.0000 0.0854
-5.250 -0.2654 0.07749 0.07203 -0.0317 1.0000 0.0849
-5.000 -0.2399 0.07179 0.06622 -0.0416 1.0000 0.0536
-4.750 -0.2390 0.06897 0.06345 -0.0377 1.0000 0.0508
-4.500 -0.2296 0.06583 0.06034 -0.0385 1.0000 0.0487
-4.250 -0.2152 0.06235 0.05683 -0.0409 0.9997 0.0466
-4.000 -0.1579 0.05497 0.04913 -0.0537 0.9897 0.0428
-3.750 -0.1110 0.05008 0.04399 -0.0615 0.9794 0.0441
-3.500 -0.0624 0.04548 0.03907 -0.0689 0.9686 0.0474
-3.250 -0.0110 0.04012 0.03321 -0.0764 0.9578 0.0484
-3.000 0.0403 0.03500 0.02736 -0.0827 0.9472 0.0501
-2.750 0.0874 0.03177 0.02357 -0.0874 0.9357 0.0582
-2.500 0.1376 0.02810 0.01889 -0.0915 0.9252 0.0665
-2.250 0.1768 0.02650 0.01700 -0.0938 0.9093 0.0859
-2.000 0.2163 0.02467 0.01455 -0.0955 0.8931 0.1096
-1.750 0.2524 0.02346 0.01315 -0.0966 0.8757 0.1342
-1.500 0.2895 0.02262 0.01203 -0.0978 0.8582 0.1598
-1.250 0.3249 0.02186 0.01095 -0.0985 0.8400 0.1779
-1.000 0.3576 0.02125 0.01013 -0.0987 0.8205 0.1954
-0.750 0.3895 0.02070 0.00945 -0.0987 0.8019 0.2151
-0.500 0.4197 0.02021 0.00886 -0.0985 0.7833 0.2418
-0.250 0.4478 0.01973 0.00849 -0.0981 0.7638 0.2998
0.000 0.4720 0.01781 0.00806 -0.0966 0.7458 1.0000
0.250 0.5002 0.01799 0.00773 -0.0960 0.7280 1.0000
0.500 0.5270 0.01822 0.00759 -0.0954 0.7097 1.0000
0.750 0.5534 0.01848 0.00754 -0.0947 0.6918 1.0000
1.000 0.5797 0.01874 0.00753 -0.0941 0.6747 1.0000
1.250 0.6060 0.01902 0.00758 -0.0935 0.6585 1.0000
1.500 0.6320 0.01932 0.00767 -0.0929 0.6428 1.0000
1.750 0.6581 0.01963 0.00781 -0.0924 0.6275 1.0000
2.000 0.6844 0.01996 0.00799 -0.0919 0.6128 1.0000
2.250 0.7106 0.02031 0.00821 -0.0915 0.5987 1.0000
2.500 0.7367 0.02067 0.00848 -0.0911 0.5850 1.0000
2.750 0.7628 0.02105 0.00882 -0.0908 0.5719 1.0000
3.000 0.7888 0.02145 0.00917 -0.0904 0.5596 1.0000
3.250 0.8149 0.02187 0.00954 -0.0901 0.5481 1.0000
3.500 0.8412 0.02227 0.00994 -0.0897 0.5377 1.0000
3.750 0.8668 0.02275 0.01046 -0.0894 0.5267 1.0000
4.000 0.8924 0.02326 0.01102 -0.0891 0.5165 1.0000
4.250 0.9186 0.02373 0.01155 -0.0888 0.5079 1.0000
4.500 0.9437 0.02426 0.01219 -0.0884 0.4979 1.0000
4.750 0.9683 0.02477 0.01280 -0.0880 0.4873 1.0000
5.000 0.9932 0.02522 0.01332 -0.0874 0.4770 1.0000
5.250 1.0179 0.02565 0.01389 -0.0868 0.4667 1.0000
5.500 1.0415 0.02621 0.01463 -0.0862 0.4560 1.0000
5.750 1.0657 0.02673 0.01531 -0.0856 0.4468 1.0000
6.000 1.0884 0.02706 0.01576 -0.0847 0.4332 1.0000
6.250 1.1068 0.02694 0.01559 -0.0827 0.4066 1.0000
6.500 1.1259 0.02725 0.01611 -0.0813 0.3853 1.0000
6.750 1.1457 0.02761 0.01658 -0.0799 0.3664 1.0000
7.000 1.1646 0.02809 0.01720 -0.0785 0.3455 1.0000
7.250 1.1845 0.02867 0.01803 -0.0773 0.3290 1.0000
7.500 1.2010 0.02930 0.01878 -0.0757 0.3012 1.0000
7.750 1.2148 0.03017 0.01970 -0.0739 0.2553 1.0000
8.000 1.2227 0.03166 0.02079 -0.0717 0.1577 1.0000
8.500 1.2111 0.03842 0.02667 -0.0666 0.0514 1.0000
8.750 1.2136 0.04065 0.02914 -0.0644 0.0387 1.0000
9.000 1.2135 0.04302 0.03175 -0.0624 0.0326 1.0000
9.250 1.2110 0.04578 0.03470 -0.0608 0.0293 1.0000
9.500 1.2059 0.04904 0.03810 -0.0599 0.0275 1.0000
9.750 1.1995 0.05275 0.04201 -0.0598 0.0265 1.0000
10.000 1.1925 0.05689 0.04637 -0.0602 0.0259 1.0000
10.250 1.1849 0.06134 0.05103 -0.0610 0.0255 1.0000
10.500 1.1771 0.06598 0.05588 -0.0620 0.0251 1.0000
10.750 1.1694 0.07068 0.06077 -0.0630 0.0248 1.0000
11.000 1.1620 0.07535 0.06562 -0.0640 0.0246 1.0000
11.250 1.1552 0.07991 0.07034 -0.0648 0.0243 1.0000
11.500 1.1493 0.08431 0.07489 -0.0655 0.0240 1.0000
11.750 1.1447 0.08845 0.07918 -0.0661 0.0238 1.0000
12.000 1.1415 0.09232 0.08319 -0.0664 0.0235 1.0000
12.250 1.1399 0.09589 0.08688 -0.0664 0.0232 1.0000
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Polar data table (+)
Polar graphs
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