GOE 437 AIRFOIL (goe437-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 437 AIRFOIL (goe437-il) Reynolds number: 200,000 Max Cl/Cd: 80.02 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe437-il-200000-n5.txt Download as CSV file: xf-goe437-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 437 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3075 0.09822 0.09500 -0.0296 1.0000 0.0178
-7.500 -0.3134 0.09632 0.09317 -0.0280 1.0000 0.0178
-7.250 -0.3195 0.09458 0.09149 -0.0263 1.0000 0.0178
-7.000 -0.3005 0.09012 0.08704 -0.0316 0.9958 0.0179
-6.750 -0.2769 0.08529 0.08220 -0.0382 0.9899 0.0179
-6.500 -0.2521 0.08049 0.07738 -0.0447 0.9837 0.0179
-6.250 -0.2252 0.07542 0.07229 -0.0517 0.9781 0.0179
-5.750 -0.1853 0.06509 0.06193 -0.0606 0.9651 0.0164
-5.500 -0.1552 0.06014 0.05692 -0.0678 0.9570 0.0163
-5.250 -0.1236 0.05505 0.05175 -0.0749 0.9486 0.0159
-5.000 -0.0889 0.04991 0.04649 -0.0820 0.9413 0.0148
-4.750 -0.0562 0.04468 0.04110 -0.0880 0.9308 0.0140
-4.500 -0.0208 0.03914 0.03533 -0.0938 0.9217 0.0135
-4.250 0.0161 0.03340 0.02927 -0.0988 0.9135 0.0130
-4.000 0.0487 0.02730 0.02271 -0.1017 0.9027 0.0128
-3.750 0.0805 0.02077 0.01536 -0.1035 0.8934 0.0129
-3.500 0.1123 0.01814 0.01214 -0.1044 0.8848 0.0149
-3.250 0.1419 0.01609 0.00954 -0.1044 0.8740 0.0163
-3.000 0.1717 0.01455 0.00759 -0.1045 0.8629 0.0174
-2.750 0.2009 0.01323 0.00599 -0.1045 0.8515 0.0206
-2.500 0.2301 0.01262 0.00521 -0.1045 0.8388 0.0262
-2.250 0.2587 0.01205 0.00449 -0.1043 0.8232 0.0347
-2.000 0.2866 0.01163 0.00391 -0.1041 0.8062 0.0487
-1.750 0.3139 0.01137 0.00355 -0.1038 0.7898 0.0666
-1.500 0.3409 0.01120 0.00333 -0.1035 0.7755 0.0820
-1.250 0.3678 0.01109 0.00311 -0.1031 0.7620 0.0994
-1.000 0.3944 0.01100 0.00290 -0.1027 0.7487 0.1169
-0.750 0.4208 0.01092 0.00276 -0.1023 0.7356 0.1349
-0.500 0.4471 0.01086 0.00265 -0.1019 0.7221 0.1502
-0.250 0.4733 0.01081 0.00255 -0.1015 0.7084 0.1685
0.000 0.4992 0.01074 0.00248 -0.1011 0.6940 0.1967
0.500 0.5626 0.00899 0.00243 -0.1028 0.6620 1.0000
0.750 0.5881 0.00911 0.00239 -0.1022 0.6445 1.0000
1.000 0.6135 0.00924 0.00236 -0.1016 0.6245 1.0000
1.250 0.6385 0.00939 0.00236 -0.1010 0.6040 1.0000
1.500 0.6634 0.00957 0.00237 -0.1003 0.5848 1.0000
1.750 0.6884 0.00975 0.00242 -0.0997 0.5681 1.0000
2.000 0.7134 0.00996 0.00249 -0.0991 0.5530 1.0000
2.250 0.7384 0.01017 0.00261 -0.0985 0.5391 1.0000
2.500 0.7634 0.01040 0.00274 -0.0979 0.5265 1.0000
2.750 0.7886 0.01063 0.00289 -0.0974 0.5150 1.0000
3.000 0.8139 0.01084 0.00308 -0.0969 0.5042 1.0000
3.250 0.8393 0.01106 0.00327 -0.0965 0.4935 1.0000
3.500 0.8645 0.01128 0.00348 -0.0960 0.4829 1.0000
3.750 0.8896 0.01152 0.00372 -0.0955 0.4722 1.0000
4.000 0.9149 0.01173 0.00396 -0.0951 0.4617 1.0000
4.250 0.9401 0.01195 0.00422 -0.0946 0.4514 1.0000
4.500 0.9650 0.01219 0.00449 -0.0941 0.4410 1.0000
4.750 0.9898 0.01244 0.00481 -0.0935 0.4304 1.0000
5.000 1.0147 0.01268 0.00512 -0.0930 0.4195 1.0000
5.250 1.0377 0.01297 0.00540 -0.0921 0.3975 1.0000
5.500 1.0579 0.01339 0.00567 -0.0909 0.3593 1.0000
5.750 1.0775 0.01395 0.00609 -0.0895 0.3170 1.0000
6.000 1.0917 0.01503 0.00667 -0.0875 0.2198 1.0000
6.250 1.0886 0.01821 0.00856 -0.0835 0.0262 1.0000
6.500 1.1065 0.01916 0.00961 -0.0818 0.0175 1.0000
6.750 1.1254 0.01996 0.01060 -0.0803 0.0150 1.0000
7.000 1.1430 0.02086 0.01171 -0.0786 0.0135 1.0000
7.250 1.1589 0.02183 0.01283 -0.0768 0.0116 1.0000
7.500 1.1700 0.02315 0.01431 -0.0744 0.0102 1.0000
7.750 1.1759 0.02478 0.01614 -0.0712 0.0097 1.0000
8.000 1.1763 0.02672 0.01817 -0.0673 0.0092 1.0000
8.250 1.1839 0.02808 0.01963 -0.0643 0.0090 1.0000
8.500 1.1915 0.02962 0.02127 -0.0615 0.0087 1.0000
8.750 1.2016 0.03108 0.02283 -0.0592 0.0082 1.0000
9.000 1.2126 0.03256 0.02441 -0.0571 0.0076 1.0000
9.250 1.2230 0.03392 0.02586 -0.0553 0.0068 1.0000
9.500 1.2351 0.03580 0.02785 -0.0535 0.0066 1.0000
9.750 1.2477 0.03782 0.02999 -0.0519 0.0064 1.0000
10.000 1.2612 0.04017 0.03246 -0.0506 0.0062 1.0000
10.250 1.2761 0.04301 0.03547 -0.0494 0.0060 1.0000
10.500 1.2881 0.04601 0.03870 -0.0481 0.0060 1.0000
10.750 1.2951 0.04920 0.04215 -0.0463 0.0059 1.0000
11.000 1.2969 0.05255 0.04576 -0.0444 0.0059 1.0000
11.250 1.2943 0.05563 0.04910 -0.0423 0.0059 1.0000
11.500 1.2889 0.05878 0.05251 -0.0404 0.0059 1.0000
11.750 1.2812 0.06211 0.05617 -0.0389 0.0059 1.0000
12.000 1.2712 0.06587 0.06018 -0.0379 0.0060 1.0000
12.250 1.2606 0.06964 0.06419 -0.0375 0.0060 1.0000
12.500 1.2489 0.07376 0.06854 -0.0376 0.0061 1.0000
12.750 1.2355 0.07838 0.07340 -0.0383 0.0061 1.0000
13.000 1.2205 0.08358 0.07884 -0.0397 0.0062 1.0000
13.250 1.2026 0.08953 0.08504 -0.0421 0.0063 1.0000
13.500 1.1809 0.09671 0.09250 -0.0456 0.0064 1.0000
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Polar data table (+)
Polar graphs
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