GOE 391 AIRFOIL (goe391-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 391 AIRFOIL (goe391-il) Reynolds number: 500,000 Max Cl/Cd: 84.48 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe391-il-500000-n5.txt Download as CSV file: xf-goe391-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 391 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4078 0.09584 0.09358 -0.0218 1.0000 0.0075
-8.000 -0.4107 0.09360 0.09138 -0.0218 1.0000 0.0076
-7.750 -0.4146 0.09128 0.08909 -0.0205 1.0000 0.0075
-6.250 -0.3312 0.06645 0.06424 -0.0469 0.9858 0.0061
-6.000 -0.3060 0.06123 0.05896 -0.0533 0.9817 0.0058
-5.750 -0.2763 0.05659 0.05425 -0.0596 0.9793 0.0066
-5.500 -0.2472 0.05240 0.04998 -0.0649 0.9767 0.0091
-5.250 -0.2180 0.04695 0.04437 -0.0695 0.9723 0.0071
-5.000 -0.1875 0.04241 0.03968 -0.0737 0.9698 0.0066
-4.750 -0.1541 0.03755 0.03462 -0.0777 0.9680 0.0063
-4.500 -0.1258 0.03303 0.02986 -0.0795 0.9637 0.0061
-4.250 -0.0956 0.02830 0.02482 -0.0810 0.9594 0.0060
-4.000 -0.0636 0.02300 0.01907 -0.0821 0.9562 0.0065
-3.750 -0.0392 0.01713 0.01254 -0.0808 0.9504 0.0071
-3.500 -0.0146 0.01215 0.00671 -0.0797 0.9457 0.0087
-3.250 0.0163 0.01144 0.00586 -0.0804 0.9425 0.0099
-3.000 0.0440 0.01069 0.00496 -0.0802 0.9379 0.0114
-2.750 0.0709 0.01010 0.00424 -0.0800 0.9326 0.0136
-2.500 0.1019 0.01001 0.00413 -0.0806 0.9286 0.0168
-2.250 0.1287 0.00974 0.00378 -0.0803 0.9219 0.0213
-2.000 0.1583 0.00984 0.00380 -0.0806 0.9164 0.0238
-1.750 0.1848 0.00921 0.00311 -0.0803 0.9105 0.0263
-1.500 0.2124 0.00903 0.00293 -0.0803 0.9035 0.0293
-1.250 0.2398 0.00874 0.00258 -0.0802 0.8970 0.0305
-1.000 0.2667 0.00850 0.00229 -0.0799 0.8899 0.0318
-0.750 0.2933 0.00821 0.00195 -0.0796 0.8797 0.0316
-0.500 0.3201 0.00798 0.00165 -0.0792 0.8668 0.0315
-0.250 0.3468 0.00780 0.00141 -0.0789 0.8552 0.0316
0.000 0.3736 0.00767 0.00123 -0.0786 0.8446 0.0318
0.250 0.4001 0.00757 0.00108 -0.0782 0.8326 0.0326
0.500 0.4265 0.00752 0.00097 -0.0778 0.8194 0.0338
0.750 0.4523 0.00747 0.00087 -0.0773 0.8004 0.0401
1.000 0.4763 0.00745 0.00084 -0.0763 0.7636 0.0819
1.500 0.5449 0.00645 0.00112 -0.0801 0.5628 1.0000
1.750 0.5657 0.00678 0.00122 -0.0787 0.5114 1.0000
2.000 0.5844 0.00729 0.00135 -0.0769 0.4276 1.0000
2.250 0.6028 0.00790 0.00155 -0.0752 0.3390 1.0000
2.500 0.6248 0.00825 0.00173 -0.0741 0.3006 1.0000
2.750 0.6470 0.00858 0.00190 -0.0731 0.2601 1.0000
3.000 0.6674 0.00912 0.00210 -0.0718 0.1853 1.0000
3.250 0.6895 0.00951 0.00235 -0.0708 0.1520 1.0000
3.500 0.7107 0.01001 0.00261 -0.0696 0.0955 1.0000
3.750 0.7317 0.01057 0.00295 -0.0684 0.0477 1.0000
4.000 0.7549 0.01089 0.00323 -0.0676 0.0388 1.0000
4.250 0.7784 0.01120 0.00355 -0.0667 0.0349 1.0000
4.500 0.8020 0.01150 0.00392 -0.0659 0.0334 1.0000
4.750 0.8257 0.01179 0.00428 -0.0651 0.0328 1.0000
5.000 0.8494 0.01207 0.00462 -0.0644 0.0315 1.0000
5.250 0.8730 0.01236 0.00496 -0.0637 0.0292 1.0000
5.500 0.8961 0.01270 0.00536 -0.0629 0.0263 1.0000
5.750 0.9182 0.01318 0.00590 -0.0619 0.0234 1.0000
6.000 0.9434 0.01327 0.00604 -0.0615 0.0213 1.0000
6.250 0.9671 0.01353 0.00626 -0.0609 0.0127 1.0000
6.500 0.9888 0.01408 0.00679 -0.0598 0.0093 1.0000
6.750 1.0095 0.01478 0.00761 -0.0585 0.0073 1.0000
7.000 1.0308 0.01536 0.00827 -0.0575 0.0060 1.0000
7.250 1.0503 0.01619 0.00921 -0.0560 0.0052 1.0000
7.500 1.0690 0.01714 0.01030 -0.0545 0.0048 1.0000
7.750 1.0879 0.01808 0.01139 -0.0530 0.0044 1.0000
8.000 1.1062 0.01913 0.01260 -0.0514 0.0042 1.0000
8.250 1.1240 0.02028 0.01391 -0.0497 0.0039 1.0000
8.500 1.1417 0.02143 0.01521 -0.0482 0.0036 1.0000
8.750 1.1595 0.02243 0.01635 -0.0469 0.0032 1.0000
9.000 1.1735 0.02417 0.01831 -0.0449 0.0030 1.0000
9.250 1.1893 0.02564 0.02005 -0.0431 0.0028 1.0000
9.500 1.2023 0.02749 0.02218 -0.0410 0.0027 1.0000
9.750 1.2116 0.02989 0.02494 -0.0384 0.0026 1.0000
10.000 1.2170 0.03265 0.02807 -0.0354 0.0024 1.0000
10.250 1.2178 0.03566 0.03147 -0.0320 0.0023 1.0000
10.500 1.2116 0.03885 0.03501 -0.0279 0.0022 1.0000
10.750 1.1938 0.04279 0.03932 -0.0226 0.0023 1.0000
11.000 1.1739 0.04676 0.04360 -0.0182 0.0022 1.0000
11.250 1.1484 0.05159 0.04873 -0.0149 0.0023 1.0000
11.500 1.1345 0.05513 0.05245 -0.0135 0.0021 1.0000
11.750 1.0928 0.06355 0.06116 -0.0142 0.0023 1.0000
12.000 1.0710 0.07023 0.06800 -0.0174 0.0023 1.0000
12.250 1.0511 0.07828 0.07618 -0.0231 0.0024 1.0000
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Polar data table (+)
Polar graphs
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