GOE 373 AIRFOIL (goe373-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 373 AIRFOIL (goe373-il) Reynolds number: 50,000 Max Cl/Cd: 41.88 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe373-il-50000-n5.txt Download as CSV file: xf-goe373-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 373 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 -0.3037 0.10468 0.09799 -0.0241 1.0000 0.0728
-7.750 -0.3105 0.10432 0.09779 -0.0253 1.0000 0.0738
-7.500 -0.3125 0.10402 0.09760 -0.0293 1.0000 0.0743
-7.250 -0.2984 0.09674 0.09034 -0.0236 1.0000 0.0781
-7.000 -0.2949 0.09426 0.08794 -0.0235 1.0000 0.0822
-6.750 -0.2939 0.09274 0.08652 -0.0254 1.0000 0.0859
-6.500 -0.2912 0.09282 0.08668 -0.0318 1.0000 0.0877
-6.250 -0.2876 0.08800 0.08195 -0.0283 1.0000 0.0896
-6.000 -0.2836 0.08473 0.07875 -0.0258 1.0000 0.0928
-5.750 -0.2798 0.08246 0.07654 -0.0259 1.0000 0.0969
-5.500 -0.2703 0.08186 0.07593 -0.0322 1.0000 0.1019
-5.250 -0.2670 0.07858 0.07273 -0.0314 1.0000 0.1037
-5.000 -0.2670 0.07549 0.06974 -0.0277 1.0000 0.1071
-4.750 -0.2587 0.07365 0.06789 -0.0293 1.0000 0.1151
-4.500 -0.2501 0.07108 0.06533 -0.0310 1.0000 0.1198
-4.250 -0.2097 0.06759 0.06168 -0.0395 0.9909 0.1340
-4.000 -0.1837 0.06352 0.05759 -0.0415 0.9823 0.1436
-3.750 -0.1473 0.05979 0.05376 -0.0473 0.9728 0.1562
-3.500 -0.1101 0.05642 0.05026 -0.0530 0.9630 0.1728
-3.250 -0.0757 0.05327 0.04701 -0.0579 0.9521 0.1975
-3.000 -0.0458 0.05027 0.04395 -0.0607 0.9417 0.2288
-2.500 0.0086 0.04480 0.03849 -0.0638 0.9210 0.3324
-2.000 0.1530 0.03887 0.03108 -0.0853 0.9033 0.1608
-1.750 0.2012 0.03613 0.02779 -0.0887 0.8921 0.1099
-1.500 0.2437 0.03407 0.02530 -0.0912 0.8808 0.0960
-1.250 0.2870 0.03227 0.02298 -0.0934 0.8693 0.0852
-1.000 0.3265 0.03044 0.02084 -0.0952 0.8570 0.0805
-0.750 0.3653 0.02911 0.01901 -0.0962 0.8431 0.0757
-0.500 0.4002 0.02798 0.01755 -0.0967 0.8283 0.0735
-0.250 0.4336 0.02681 0.01614 -0.0972 0.8134 0.0722
0.000 0.4651 0.02593 0.01502 -0.0972 0.7983 0.0721
0.250 0.4955 0.02526 0.01409 -0.0969 0.7831 0.0732
0.500 0.5260 0.02468 0.01324 -0.0966 0.7678 0.0740
0.750 0.5563 0.02411 0.01246 -0.0963 0.7526 0.0740
1.000 0.5851 0.02363 0.01182 -0.0958 0.7375 0.0740
1.250 0.6128 0.02325 0.01131 -0.0951 0.7221 0.0743
1.500 0.6399 0.02294 0.01090 -0.0945 0.7069 0.0749
1.750 0.6667 0.02271 0.01059 -0.0939 0.6918 0.0761
2.000 0.6933 0.02258 0.01038 -0.0933 0.6768 0.0779
2.250 0.7199 0.02253 0.01027 -0.0928 0.6619 0.0812
2.500 0.7462 0.02257 0.01021 -0.0922 0.6472 0.0878
2.750 0.7725 0.02258 0.01023 -0.0917 0.6328 0.0976
3.000 0.7989 0.02260 0.01036 -0.0911 0.6188 0.1173
3.250 0.8253 0.02134 0.01056 -0.0908 0.6053 1.0000
3.500 0.8511 0.02169 0.01072 -0.0900 0.5921 1.0000
3.750 0.8770 0.02205 0.01093 -0.0894 0.5794 1.0000
4.000 0.9031 0.02242 0.01118 -0.0887 0.5674 1.0000
4.250 0.9281 0.02286 0.01156 -0.0880 0.5544 1.0000
4.500 0.9526 0.02332 0.01198 -0.0873 0.5409 1.0000
4.750 0.9767 0.02376 0.01238 -0.0864 0.5266 1.0000
5.000 1.0004 0.02418 0.01279 -0.0855 0.5112 1.0000
5.250 1.0234 0.02460 0.01319 -0.0844 0.4953 1.0000
5.500 1.0462 0.02505 0.01365 -0.0834 0.4800 1.0000
5.750 1.0691 0.02558 0.01427 -0.0825 0.4665 1.0000
6.000 1.0919 0.02612 0.01489 -0.0816 0.4536 1.0000
6.250 1.1148 0.02665 0.01551 -0.0807 0.4410 1.0000
6.500 1.1375 0.02716 0.01611 -0.0797 0.4283 1.0000
6.750 1.1595 0.02770 0.01679 -0.0787 0.4151 1.0000
7.000 1.1806 0.02831 0.01756 -0.0776 0.4013 1.0000
7.250 1.2012 0.02889 0.01827 -0.0764 0.3867 1.0000
7.500 1.2193 0.02933 0.01877 -0.0747 0.3673 1.0000
7.750 1.2353 0.02987 0.01944 -0.0729 0.3458 1.0000
8.000 1.2510 0.03040 0.01996 -0.0710 0.3245 1.0000
8.250 1.2629 0.03113 0.02077 -0.0688 0.2992 1.0000
8.500 1.2761 0.03192 0.02161 -0.0669 0.2783 1.0000
8.750 1.2904 0.03284 0.02273 -0.0653 0.2610 1.0000
9.000 1.3028 0.03383 0.02389 -0.0634 0.2419 1.0000
9.250 1.3130 0.03490 0.02511 -0.0615 0.2230 1.0000
9.500 1.3193 0.03617 0.02639 -0.0592 0.2008 1.0000
9.750 1.3221 0.03767 0.02784 -0.0567 0.1817 1.0000
10.000 1.3241 0.03935 0.02956 -0.0543 0.1668 1.0000
10.250 1.3235 0.04136 0.03162 -0.0521 0.1508 1.0000
10.500 1.3200 0.04383 0.03415 -0.0503 0.1267 1.0000
10.750 1.3144 0.04675 0.03707 -0.0491 0.0968 1.0000
11.000 1.3040 0.05042 0.04061 -0.0484 0.0737 1.0000
11.250 1.2936 0.05446 0.04466 -0.0482 0.0617 1.0000
11.500 1.2823 0.05892 0.04913 -0.0486 0.0540 1.0000
11.750 1.2736 0.06335 0.05368 -0.0492 0.0478 1.0000
12.000 1.2632 0.06822 0.05865 -0.0503 0.0442 1.0000
12.250 1.2540 0.07312 0.06369 -0.0515 0.0417 1.0000
12.500 1.2455 0.07807 0.06881 -0.0528 0.0398 1.0000
12.750 1.2368 0.08318 0.07408 -0.0543 0.0384 1.0000
13.000 1.2278 0.08842 0.07947 -0.0560 0.0372 1.0000
13.250 1.2191 0.09372 0.08490 -0.0577 0.0362 1.0000
13.500 1.2110 0.09903 0.09033 -0.0596 0.0354 1.0000
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Polar data table (+)
Polar graphs
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