GOE 766 AIRFOIL (goe766-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 766 AIRFOIL (goe766-il) Reynolds number: 50,000 Max Cl/Cd: 27.37 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe766-il-50000-n5.txt Download as CSV file: xf-goe766-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 766 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6570 0.08049 0.07251 -0.0268 1.0000 0.0778
-10.250 -0.6825 0.07445 0.06642 -0.0296 1.0000 0.0775
-10.000 -0.7080 0.06968 0.06156 -0.0297 1.0000 0.0773
-9.750 -0.7296 0.06533 0.05704 -0.0286 1.0000 0.0774
-9.500 -0.7474 0.06097 0.05239 -0.0272 1.0000 0.0777
-9.250 -0.7556 0.05720 0.04835 -0.0256 1.0000 0.0784
-9.000 -0.7456 0.05501 0.04612 -0.0245 1.0000 0.0798
-8.750 -0.7386 0.05254 0.04352 -0.0230 1.0000 0.0810
-8.500 -0.7331 0.04974 0.04048 -0.0214 1.0000 0.0821
-8.250 -0.7262 0.04689 0.03734 -0.0197 1.0000 0.0831
-8.000 -0.7170 0.04418 0.03432 -0.0180 1.0000 0.0843
-7.750 -0.7056 0.04172 0.03151 -0.0162 1.0000 0.0863
-7.500 -0.6930 0.03933 0.02867 -0.0144 1.0000 0.0886
-7.250 -0.6761 0.03742 0.02656 -0.0130 1.0000 0.0908
-7.000 -0.6568 0.03590 0.02499 -0.0118 1.0000 0.0930
-6.750 -0.6372 0.03430 0.02324 -0.0106 1.0000 0.0953
-6.500 -0.6169 0.03277 0.02149 -0.0093 1.0000 0.0987
-6.250 -0.5959 0.03136 0.01989 -0.0080 1.0000 0.1026
-6.000 -0.5748 0.03028 0.01887 -0.0069 1.0000 0.1066
-5.750 -0.5524 0.02911 0.01758 -0.0057 1.0000 0.1112
-5.500 -0.5301 0.02803 0.01647 -0.0046 1.0000 0.1168
-5.250 -0.5085 0.02714 0.01559 -0.0034 1.0000 0.1238
-5.000 -0.4864 0.02619 0.01465 -0.0022 1.0000 0.1316
-4.750 -0.4646 0.02536 0.01376 -0.0009 1.0000 0.1427
-4.500 -0.4441 0.02448 0.01302 0.0004 1.0000 0.1554
-4.250 -0.4239 0.02363 0.01226 0.0017 1.0000 0.1724
-4.000 -0.4045 0.02279 0.01155 0.0031 1.0000 0.1943
-3.750 -0.3867 0.02195 0.01094 0.0047 1.0000 0.2221
-3.500 -0.3695 0.02114 0.01042 0.0062 1.0000 0.2590
-3.250 -0.3552 0.02032 0.01005 0.0082 1.0000 0.3134
-3.000 -0.3440 0.01951 0.00984 0.0109 1.0000 0.4020
-2.750 -0.3253 0.01870 0.01001 0.0128 0.9921 0.5549
-2.500 -0.2794 0.01852 0.01039 0.0112 0.9697 0.7089
-2.250 -0.2244 0.01868 0.01063 0.0079 0.9455 0.7874
-2.000 -0.1624 0.01890 0.01074 0.0031 0.9183 0.8378
-1.750 -0.0981 0.01910 0.01075 -0.0023 0.8844 0.8735
-1.500 -0.0117 0.01953 0.01091 -0.0109 0.8412 0.9137
-1.250 0.0612 0.01971 0.01071 -0.0177 0.7857 0.9429
-1.000 0.1106 0.01970 0.01030 -0.0211 0.7350 0.9583
-0.750 0.1526 0.01970 0.00994 -0.0235 0.6940 0.9718
-0.500 0.1945 0.01969 0.00960 -0.0262 0.6591 0.9849
-0.250 0.2381 0.01963 0.00926 -0.0295 0.6287 0.9987
0.000 0.2594 0.01969 0.00911 -0.0287 0.6066 1.0000
0.250 0.2784 0.01977 0.00903 -0.0274 0.5864 1.0000
0.500 0.2979 0.01987 0.00899 -0.0261 0.5680 1.0000
0.750 0.3177 0.02000 0.00898 -0.0249 0.5513 1.0000
1.000 0.3377 0.02017 0.00901 -0.0236 0.5358 1.0000
1.250 0.3578 0.02035 0.00910 -0.0223 0.5206 1.0000
1.500 0.3782 0.02057 0.00925 -0.0211 0.5061 1.0000
1.750 0.3989 0.02081 0.00943 -0.0200 0.4925 1.0000
2.000 0.4204 0.02109 0.00961 -0.0189 0.4799 1.0000
2.250 0.4418 0.02138 0.00984 -0.0178 0.4677 1.0000
2.500 0.4631 0.02172 0.01017 -0.0167 0.4555 1.0000
2.750 0.4846 0.02207 0.01044 -0.0156 0.4449 1.0000
3.000 0.5059 0.02245 0.01081 -0.0144 0.4338 1.0000
3.250 0.5272 0.02288 0.01123 -0.0133 0.4234 1.0000
3.500 0.5488 0.02329 0.01160 -0.0121 0.4142 1.0000
3.750 0.5699 0.02379 0.01215 -0.0110 0.4043 1.0000
4.000 0.5917 0.02423 0.01253 -0.0099 0.3960 1.0000
4.250 0.6124 0.02480 0.01319 -0.0088 0.3862 1.0000
4.500 0.6343 0.02526 0.01360 -0.0076 0.3786 1.0000
4.750 0.6545 0.02590 0.01437 -0.0065 0.3693 1.0000
5.000 0.6763 0.02636 0.01479 -0.0053 0.3616 1.0000
5.250 0.6960 0.02705 0.01561 -0.0041 0.3523 1.0000
5.500 0.7178 0.02748 0.01601 -0.0029 0.3445 1.0000
5.750 0.7366 0.02820 0.01688 -0.0015 0.3347 1.0000
6.000 0.7587 0.02855 0.01716 -0.0003 0.3270 1.0000
6.250 0.7763 0.02933 0.01815 0.0011 0.3165 1.0000
6.500 0.7968 0.02980 0.01861 0.0024 0.3079 1.0000
6.750 0.8154 0.03041 0.01933 0.0038 0.2978 1.0000
7.000 0.8337 0.03106 0.02007 0.0053 0.2879 1.0000
7.250 0.8546 0.03137 0.02033 0.0066 0.2785 1.0000
7.500 0.8702 0.03218 0.02134 0.0082 0.2671 1.0000
7.750 0.8877 0.03276 0.02197 0.0097 0.2564 1.0000
8.000 0.9069 0.03313 0.02230 0.0112 0.2461 1.0000
8.250 0.9202 0.03408 0.02345 0.0129 0.2341 1.0000
8.500 0.9350 0.03489 0.02434 0.0145 0.2233 1.0000
8.750 0.9528 0.03532 0.02468 0.0160 0.2134 1.0000
9.000 0.9621 0.03663 0.02626 0.0179 0.2020 1.0000
9.250 0.9730 0.03774 0.02748 0.0197 0.1919 1.0000
9.500 0.9876 0.03842 0.02809 0.0213 0.1832 1.0000
9.750 0.9915 0.04020 0.03011 0.0233 0.1737 1.0000
10.000 1.0011 0.04129 0.03120 0.0251 0.1662 1.0000
10.250 1.0034 0.04307 0.03315 0.0270 0.1588 1.0000
10.500 1.0108 0.04434 0.03439 0.0287 0.1530 1.0000
10.750 1.0028 0.04681 0.03707 0.0310 0.1478 1.0000
11.000 1.0060 0.04825 0.03848 0.0327 0.1430 1.0000
11.250 1.0001 0.05081 0.04114 0.0339 0.1390 1.0000
11.500 0.9803 0.05512 0.04566 0.0338 0.1358 1.0000
11.750 0.9647 0.05957 0.05025 0.0327 0.1328 1.0000
12.000 0.9838 0.05985 0.05040 0.0340 0.1287 1.0000
12.250 0.9468 0.06787 0.05866 0.0300 0.1270 1.0000
12.500 0.7966 0.09877 0.08979 0.0112 0.1249 1.0000
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Polar data table (+)
Polar graphs
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