GOE 510 AIRFOIL (goe510-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 510 AIRFOIL (goe510-il) Reynolds number: 50,000 Max Cl/Cd: 29.53 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe510-il-50000-n5.txt Download as CSV file: xf-goe510-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 510 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
------ -------- --------- --------- -------- -------- --------
-7.000 -0.2442 0.10573 0.09936 -0.0422 0.9601 0.1620
-6.750 -0.2643 0.10454 0.09819 -0.0464 0.9467 0.1653
-6.500 -0.2680 0.10205 0.09566 -0.0504 0.9347 0.1660
-6.000 -0.2509 0.08705 0.08033 -0.0593 0.9172 0.1034
-5.750 -0.2297 0.08374 0.07701 -0.0603 0.9113 0.1014
-5.500 -0.2207 0.08046 0.07368 -0.0612 0.9004 0.1005
-5.250 -0.2095 0.07707 0.07019 -0.0625 0.8895 0.0997
-4.750 -0.1776 0.06954 0.06236 -0.0662 0.8692 0.0967
-4.250 -0.1459 0.05850 0.05038 -0.0708 0.8506 0.0904
-4.000 -0.1342 0.05577 0.04743 -0.0696 0.8392 0.0903
-3.750 -0.1049 0.05336 0.04492 -0.0710 0.8335 0.0918
-3.500 -0.0928 0.05186 0.04332 -0.0692 0.8218 0.0930
-3.250 -0.0616 0.04907 0.04022 -0.0707 0.8166 0.0943
-3.000 -0.0502 0.04699 0.03783 -0.0686 0.8046 0.0943
-2.750 -0.0173 0.04402 0.03442 -0.0699 0.7997 0.0946
-2.500 -0.0037 0.04249 0.03258 -0.0677 0.7876 0.0950
-2.250 0.0324 0.04034 0.03004 -0.0690 0.7828 0.0973
-2.000 0.0479 0.03931 0.02873 -0.0670 0.7705 0.0997
-1.750 0.0868 0.03726 0.02619 -0.0683 0.7659 0.1023
-1.500 0.1053 0.03643 0.02504 -0.0666 0.7536 0.1034
-1.250 0.1471 0.03484 0.02327 -0.0684 0.7488 0.1056
-1.000 0.1666 0.03441 0.02278 -0.0668 0.7362 0.1082
-0.750 0.2030 0.03356 0.02175 -0.0679 0.7283 0.1134
-0.500 0.2423 0.03279 0.02073 -0.0694 0.7190 0.1188
-0.250 0.2791 0.03214 0.02005 -0.0706 0.7098 0.1237
0.000 0.3189 0.03139 0.01918 -0.0720 0.7013 0.1317
0.250 0.3473 0.03104 0.01887 -0.0718 0.6904 0.1420
0.500 0.3884 0.03022 0.01808 -0.0734 0.6831 0.1615
0.750 0.4108 0.03002 0.01801 -0.0721 0.6710 0.1859
1.000 0.4519 0.02934 0.01741 -0.0736 0.6640 0.2528
1.250 0.4705 0.02944 0.01750 -0.0718 0.6515 0.2953
1.500 0.4952 0.02928 0.01736 -0.0711 0.6410 0.3415
1.750 0.5270 0.02861 0.01681 -0.0714 0.6322 0.4015
2.000 0.5406 0.02818 0.01677 -0.0690 0.6209 0.4650
2.500 0.7305 0.02755 0.01656 -0.0938 0.5986 1.0000
2.750 0.7477 0.02794 0.01679 -0.0919 0.5879 1.0000
3.000 0.7780 0.02802 0.01665 -0.0920 0.5791 1.0000
3.250 0.7874 0.02861 0.01715 -0.0888 0.5683 1.0000
3.500 0.8190 0.02867 0.01700 -0.0892 0.5604 1.0000
3.750 0.8249 0.02937 0.01766 -0.0855 0.5503 1.0000
4.000 0.8541 0.02951 0.01762 -0.0855 0.5429 1.0000
4.250 0.8599 0.03021 0.01830 -0.0819 0.5333 1.0000
4.500 0.8904 0.03034 0.01827 -0.0821 0.5264 1.0000
4.750 0.8921 0.03116 0.01910 -0.0778 0.5175 1.0000
5.000 0.9238 0.03128 0.01907 -0.0783 0.5108 1.0000
5.250 0.9231 0.03216 0.01999 -0.0737 0.5025 1.0000
5.500 0.9489 0.03244 0.02017 -0.0733 0.4958 1.0000
5.750 0.9565 0.03318 0.02090 -0.0700 0.4885 1.0000
6.000 0.9715 0.03373 0.02142 -0.0680 0.4814 1.0000
6.250 0.9987 0.03403 0.02164 -0.0678 0.4754 1.0000
6.500 0.9950 0.03516 0.02283 -0.0631 0.4680 1.0000
6.750 1.0235 0.03541 0.02301 -0.0631 0.4620 1.0000
7.000 1.0267 0.03644 0.02409 -0.0595 0.4553 1.0000
7.250 1.0355 0.03733 0.02500 -0.0568 0.4485 1.0000
7.500 1.0732 0.03735 0.02493 -0.0581 0.4434 1.0000
7.750 1.0546 0.03923 0.02695 -0.0520 0.4362 1.0000
8.000 1.0699 0.03999 0.02773 -0.0503 0.4301 1.0000
8.250 1.1063 0.04001 0.02769 -0.0513 0.4251 1.0000
8.500 1.0732 0.04282 0.03069 -0.0442 0.4176 1.0000
8.750 1.0926 0.04345 0.03134 -0.0431 0.4120 1.0000
9.000 1.1221 0.04370 0.03156 -0.0432 0.4072 1.0000
9.250 1.0717 0.04803 0.03610 -0.0357 0.3987 1.0000
9.500 1.0978 0.04825 0.03635 -0.0352 0.3939 1.0000
9.750 1.0821 0.05121 0.03941 -0.0317 0.3873 1.0000
10.000 1.0426 0.05630 0.04463 -0.0276 0.3783 1.0000
10.250 1.0839 0.05515 0.04348 -0.0277 0.3752 1.0000
10.500 0.9853 0.06684 0.05534 -0.0237 0.3605 1.0000
10.750 1.0209 0.06560 0.05413 -0.0228 0.3581 1.0000
11.250 0.9757 0.07642 0.06510 -0.0214 0.3408 1.0000
11.750 0.9376 0.08769 0.07650 -0.0216 0.3230 1.0000
12.250 0.9252 0.09574 0.08468 -0.0217 0.3084 1.0000
12.750 0.9059 0.10495 0.09400 -0.0225 0.2933 1.0000
13.250 0.8926 0.11337 0.10253 -0.0236 0.2789 1.0000
13.500 0.9176 0.11288 0.10213 -0.0224 0.2765 1.0000
13.750 0.8841 0.12125 0.11053 -0.0248 0.2654 1.0000
14.000 0.9026 0.12176 0.11112 -0.0241 0.2621 1.0000
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Polar data table (+)
Polar graphs
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