GOE 403 AIRFOIL (goe403-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 403 AIRFOIL (goe403-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.87 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe403-il-1000000-n5.txt Download as CSV file: xf-goe403-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 403 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3596 0.09567 0.09412 -0.0238 1.0000 0.0021
-8.500 -0.3605 0.09151 0.08998 -0.0247 1.0000 0.0023
-8.250 -0.3606 0.08822 0.08672 -0.0254 1.0000 0.0023
-8.000 -0.3576 0.08408 0.08261 -0.0277 0.9988 0.0023
-7.500 -0.3303 0.07502 0.07356 -0.0387 0.9708 0.0026
-7.000 -0.2977 0.01783 0.01455 -0.0978 0.8747 0.0024
-6.750 -0.2775 0.01485 0.01098 -0.0976 0.8516 0.0025
-6.500 -0.2537 0.01361 0.00947 -0.0973 0.8361 0.0028
-6.250 -0.2286 0.01286 0.00853 -0.0971 0.8253 0.0030
-5.750 -0.1772 0.01127 0.00648 -0.0965 0.8089 0.0034
-5.500 -0.1511 0.01062 0.00562 -0.0962 0.8015 0.0037
-5.250 -0.1244 0.01013 0.00499 -0.0960 0.7946 0.0040
-5.000 -0.0981 0.00954 0.00421 -0.0957 0.7875 0.0045
-4.750 -0.0713 0.00908 0.00364 -0.0955 0.7805 0.0052
-4.250 -0.0174 0.00847 0.00282 -0.0950 0.7658 0.0072
-4.000 0.0094 0.00814 0.00243 -0.0948 0.7582 0.0102
-3.750 0.0364 0.00792 0.00222 -0.0946 0.7493 0.0184
-3.500 0.0636 0.00779 0.00204 -0.0944 0.7399 0.0229
-3.250 0.0907 0.00772 0.00193 -0.0942 0.7290 0.0277
-3.000 0.1179 0.00769 0.00183 -0.0940 0.7161 0.0303
-2.750 0.1450 0.00771 0.00179 -0.0938 0.7012 0.0318
-2.500 0.1719 0.00769 0.00168 -0.0936 0.6825 0.0327
-2.000 0.2245 0.00755 0.00126 -0.0929 0.6341 0.0348
-1.750 0.2508 0.00755 0.00113 -0.0925 0.6071 0.0357
-1.500 0.2772 0.00758 0.00102 -0.0922 0.5819 0.0365
-1.250 0.3038 0.00760 0.00094 -0.0919 0.5615 0.0375
-1.000 0.3305 0.00761 0.00088 -0.0917 0.5446 0.0389
-0.750 0.3574 0.00762 0.00083 -0.0915 0.5308 0.0415
-0.500 0.3844 0.00761 0.00079 -0.0913 0.5190 0.0492
-0.250 0.4113 0.00756 0.00078 -0.0912 0.5088 0.0710
0.000 0.4383 0.00755 0.00079 -0.0910 0.4994 0.0907
0.250 0.4654 0.00757 0.00079 -0.0909 0.4906 0.1012
0.500 0.4926 0.00758 0.00081 -0.0908 0.4831 0.1103
1.000 0.5468 0.00759 0.00086 -0.0905 0.4664 0.1416
1.250 0.5736 0.00759 0.00091 -0.0903 0.4577 0.1695
1.500 0.6003 0.00754 0.00098 -0.0902 0.4481 0.2293
1.750 0.6269 0.00750 0.00106 -0.0901 0.4375 0.2908
2.000 0.6456 0.00654 0.00125 -0.0887 0.4144 0.7986
2.500 0.7098 0.00658 0.00145 -0.0908 0.3634 1.0000
2.750 0.7336 0.00699 0.00161 -0.0901 0.3124 1.0000
3.000 0.7516 0.00811 0.00207 -0.0887 0.1781 1.0000
3.250 0.7689 0.00942 0.00274 -0.0871 0.0174 1.0000
3.500 0.7949 0.00962 0.00296 -0.0867 0.0116 1.0000
3.750 0.8208 0.00982 0.00318 -0.0864 0.0099 1.0000
4.000 0.8464 0.01006 0.00345 -0.0860 0.0082 1.0000
4.250 0.8713 0.01041 0.00384 -0.0854 0.0066 1.0000
4.500 0.8968 0.01065 0.00411 -0.0850 0.0056 1.0000
4.750 0.9217 0.01097 0.00444 -0.0845 0.0050 1.0000
5.000 0.9454 0.01143 0.00494 -0.0838 0.0043 1.0000
5.250 0.9690 0.01192 0.00550 -0.0830 0.0040 1.0000
5.500 0.9922 0.01245 0.00610 -0.0822 0.0036 1.0000
5.750 1.0159 0.01287 0.00657 -0.0815 0.0031 1.0000
6.000 1.0394 0.01328 0.00701 -0.0809 0.0028 1.0000
6.250 1.0620 0.01380 0.00756 -0.0801 0.0026 1.0000
6.500 1.0796 0.01489 0.00876 -0.0784 0.0024 1.0000
6.750 1.0996 0.01566 0.00962 -0.0771 0.0023 1.0000
7.000 1.1166 0.01677 0.01085 -0.0753 0.0021 1.0000
7.250 1.1307 0.01837 0.01257 -0.0729 0.0019 1.0000
7.500 1.1458 0.02041 0.01472 -0.0705 0.0017 1.0000
7.750 1.1650 0.02268 0.01716 -0.0689 0.0017 1.0000
8.000 1.1865 0.02518 0.01981 -0.0676 0.0017 1.0000
8.250 1.2072 0.02781 0.02263 -0.0662 0.0018 1.0000
8.500 1.2253 0.03068 0.02574 -0.0645 0.0018 1.0000
8.750 1.2404 0.03359 0.02890 -0.0625 0.0019 1.0000
9.000 1.2546 0.03609 0.03162 -0.0606 0.0017 1.0000
9.250 1.2653 0.03886 0.03463 -0.0583 0.0017 1.0000
9.500 1.2751 0.04086 0.03679 -0.0564 0.0015 1.0000
9.750 1.2804 0.04371 0.03986 -0.0538 0.0015 1.0000
10.000 1.2817 0.04675 0.04313 -0.0509 0.0015 1.0000
10.250 1.2786 0.04980 0.04640 -0.0478 0.0015 1.0000
10.500 1.2745 0.05131 0.04801 -0.0446 0.0014 1.0000
10.750 1.2566 0.05506 0.05199 -0.0400 0.0014 1.0000
11.000 1.2450 0.05722 0.05427 -0.0373 0.0014 1.0000
11.250 1.2279 0.06083 0.05804 -0.0352 0.0014 1.0000
11.500 1.2163 0.06357 0.06089 -0.0344 0.0014 1.0000
11.750 1.1989 0.06788 0.06534 -0.0343 0.0014 1.0000
12.000 1.1692 0.07508 0.07277 -0.0353 0.0015 1.0000
12.250 1.1534 0.08004 0.07785 -0.0374 0.0014 1.0000
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Polar data table (+)
Polar graphs
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