GOE 371 AIRFOIL (goe371-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 371 AIRFOIL (goe371-il) Reynolds number: 100,000 Max Cl/Cd: 61.09 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe371-il-100000.txt Download as CSV file: xf-goe371-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 371 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3348 0.09989 0.09509 -0.0292 1.0000 0.0602
-7.750 -0.3434 0.09900 0.09433 -0.0295 1.0000 0.0606
-7.500 -0.3483 0.09807 0.09351 -0.0331 1.0000 0.0609
-7.250 -0.3489 0.09662 0.09211 -0.0371 1.0000 0.0612
-7.000 -0.3397 0.08909 0.08462 -0.0271 1.0000 0.0635
-6.750 -0.3381 0.08653 0.08212 -0.0253 1.0000 0.0652
-6.500 -0.3398 0.08440 0.08006 -0.0243 1.0000 0.0671
-6.250 -0.3431 0.08240 0.07813 -0.0238 1.0000 0.0694
-6.000 -0.3460 0.08057 0.07635 -0.0242 1.0000 0.0716
-5.750 -0.3416 0.07955 0.07530 -0.0311 1.0000 0.0742
-5.500 -0.3338 0.07679 0.07246 -0.0357 1.0000 0.0752
-5.250 -0.3395 0.07292 0.06874 -0.0294 1.0000 0.0766
-5.000 -0.3386 0.07042 0.06629 -0.0263 1.0000 0.0788
-4.750 -0.3316 0.06799 0.06386 -0.0263 1.0000 0.0830
-4.500 -0.3040 0.06448 0.06012 -0.0354 1.0000 0.0902
-4.250 -0.3038 0.06177 0.05751 -0.0312 1.0000 0.0933
-4.000 -0.2688 0.05905 0.05440 -0.0397 1.0000 0.1042
-3.750 -0.2657 0.05560 0.05113 -0.0365 1.0000 0.1066
-3.500 -0.2206 0.05175 0.04702 -0.0441 0.9950 0.1200
-3.250 -0.1816 0.04829 0.04338 -0.0493 0.9891 0.1346
-3.000 -0.1464 0.04511 0.04016 -0.0528 0.9838 0.1520
-2.750 -0.1073 0.04246 0.03725 -0.0575 0.9769 0.1786
-2.500 -0.0682 0.03981 0.03448 -0.0614 0.9712 0.2078
-1.500 0.1185 0.02780 0.02025 -0.0760 0.9460 0.1210
-1.250 0.1656 0.02583 0.01781 -0.0789 0.9407 0.1096
-1.000 0.2027 0.02466 0.01614 -0.0798 0.9316 0.1020
-0.750 0.2467 0.02324 0.01448 -0.0824 0.9251 0.0990
-0.500 0.2848 0.02222 0.01331 -0.0838 0.9161 0.0983
-0.250 0.3242 0.02142 0.01240 -0.0855 0.9073 0.1007
0.000 0.3703 0.02043 0.01146 -0.0885 0.9001 0.1075
0.250 0.4080 0.01975 0.01083 -0.0899 0.8898 0.1136
0.500 0.4583 0.01887 0.00997 -0.0933 0.8840 0.1294
0.750 0.5111 0.01625 0.00935 -0.0977 0.8750 1.0000
1.000 0.5493 0.01607 0.00893 -0.0989 0.8635 1.0000
1.250 0.5873 0.01584 0.00855 -0.1000 0.8519 1.0000
1.500 0.6232 0.01561 0.00822 -0.1006 0.8396 1.0000
1.750 0.6537 0.01550 0.00802 -0.1002 0.8242 1.0000
2.000 0.6822 0.01545 0.00790 -0.0995 0.8075 1.0000
2.250 0.7103 0.01540 0.00778 -0.0987 0.7899 1.0000
2.500 0.7385 0.01528 0.00759 -0.0977 0.7715 1.0000
2.750 0.7661 0.01516 0.00736 -0.0965 0.7525 1.0000
3.000 0.7900 0.01517 0.00730 -0.0949 0.7297 1.0000
3.250 0.8161 0.01518 0.00721 -0.0938 0.7106 1.0000
3.500 0.8408 0.01533 0.00736 -0.0927 0.6919 1.0000
3.750 0.8653 0.01551 0.00753 -0.0917 0.6738 1.0000
4.000 0.8902 0.01567 0.00767 -0.0907 0.6565 1.0000
4.250 0.9153 0.01582 0.00780 -0.0897 0.6395 1.0000
4.500 0.9405 0.01596 0.00794 -0.0888 0.6227 1.0000
4.750 0.9644 0.01618 0.00819 -0.0877 0.6042 1.0000
5.000 0.9887 0.01639 0.00841 -0.0867 0.5858 1.0000
5.250 1.0134 0.01663 0.00863 -0.0857 0.5669 1.0000
5.500 1.0367 0.01697 0.00898 -0.0845 0.5457 1.0000
5.750 1.0605 0.01738 0.00933 -0.0834 0.5237 1.0000
6.000 1.0823 0.01785 0.00979 -0.0820 0.4974 1.0000
6.250 1.1027 0.01832 0.01020 -0.0803 0.4668 1.0000
6.500 1.1220 0.01880 0.01062 -0.0784 0.4342 1.0000
6.750 1.1399 0.01928 0.01113 -0.0765 0.3994 1.0000
7.000 1.1584 0.01983 0.01167 -0.0747 0.3666 1.0000
7.250 1.1763 0.02040 0.01219 -0.0728 0.3354 1.0000
7.500 1.1930 0.02101 0.01274 -0.0709 0.3047 1.0000
7.750 1.2083 0.02173 0.01339 -0.0690 0.2727 1.0000
8.000 1.2228 0.02264 0.01420 -0.0670 0.2434 1.0000
8.250 1.2367 0.02367 0.01516 -0.0651 0.2163 1.0000
8.500 1.2488 0.02471 0.01620 -0.0629 0.1869 1.0000
8.750 1.2578 0.02588 0.01733 -0.0604 0.1514 1.0000
9.000 1.2593 0.02780 0.01895 -0.0570 0.0984 1.0000
9.250 1.2584 0.03025 0.02114 -0.0531 0.0747 1.0000
9.500 1.2621 0.03233 0.02320 -0.0497 0.0644 1.0000
9.750 1.2688 0.03448 0.02534 -0.0471 0.0579 1.0000
10.000 1.2801 0.03641 0.02734 -0.0450 0.0529 1.0000
10.250 1.3035 0.03976 0.03059 -0.0448 0.0489 1.0000
10.500 1.3235 0.04226 0.03342 -0.0436 0.0470 1.0000
10.750 1.3387 0.04489 0.03635 -0.0421 0.0448 1.0000
11.000 1.3483 0.04733 0.03906 -0.0402 0.0426 1.0000
11.250 1.3565 0.04993 0.04183 -0.0384 0.0409 1.0000
11.500 1.3651 0.05349 0.04560 -0.0370 0.0399 1.0000
11.750 1.3659 0.05719 0.04962 -0.0348 0.0396 1.0000
12.000 1.3599 0.06072 0.05347 -0.0322 0.0395 1.0000
12.250 1.3489 0.06434 0.05741 -0.0297 0.0396 1.0000
12.500 1.3339 0.06796 0.06135 -0.0277 0.0397 1.0000
12.750 1.3155 0.07198 0.06569 -0.0264 0.0400 1.0000
13.000 1.2940 0.07668 0.07070 -0.0261 0.0403 1.0000
13.250 1.2681 0.08223 0.07657 -0.0271 0.0409 1.0000
13.500 1.2343 0.08928 0.08394 -0.0301 0.0415 1.0000
13.750 1.1986 0.09789 0.09283 -0.0351 0.0422 1.0000
14.000 1.1607 0.10855 0.10372 -0.0423 0.0433 1.0000
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Polar data table (+)
Polar graphs
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