S9027 (8%) (s9027-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9027 (8%) (s9027-il) Reynolds number: 50,000 Max Cl/Cd: 23.89 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9027-il-50000-n5.txt Download as CSV file: xf-s9027-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S9027 (8%)
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.7206 0.09052 0.08334 0.0021 1.0000 0.0621
-9.750 -0.7389 0.08118 0.07406 -0.0049 1.0000 0.0612
-9.500 -0.8108 0.06632 0.05902 -0.0159 1.0000 0.0560
-9.250 -0.8118 0.06288 0.05549 -0.0161 1.0000 0.0573
-9.000 -0.8098 0.05971 0.05220 -0.0162 1.0000 0.0592
-8.750 -0.8109 0.05569 0.04791 -0.0164 1.0000 0.0611
-8.500 -0.8107 0.05125 0.04306 -0.0163 1.0000 0.0631
-8.250 -0.8066 0.04680 0.03805 -0.0159 1.0000 0.0650
-8.000 -0.7975 0.04259 0.03318 -0.0152 1.0000 0.0668
-7.750 -0.7820 0.03950 0.02971 -0.0144 1.0000 0.0692
-7.500 -0.7635 0.03761 0.02770 -0.0137 1.0000 0.0737
-7.250 -0.7451 0.03517 0.02468 -0.0129 1.0000 0.0800
-7.000 -0.7244 0.03328 0.02276 -0.0122 1.0000 0.0851
-6.750 -0.7026 0.03132 0.02044 -0.0113 1.0000 0.0921
-6.500 -0.6812 0.02991 0.01899 -0.0106 1.0000 0.1013
-6.250 -0.6584 0.02833 0.01719 -0.0097 1.0000 0.1110
-6.000 -0.6358 0.02707 0.01580 -0.0090 1.0000 0.1237
-5.750 -0.6127 0.02586 0.01452 -0.0082 1.0000 0.1374
-5.500 -0.5896 0.02474 0.01338 -0.0074 1.0000 0.1531
-5.250 -0.5664 0.02372 0.01234 -0.0066 1.0000 0.1726
-5.000 -0.5427 0.02272 0.01129 -0.0058 1.0000 0.1935
-4.750 -0.5192 0.02184 0.01045 -0.0051 1.0000 0.2207
-4.500 -0.4957 0.02099 0.00970 -0.0044 1.0000 0.2509
-4.250 -0.4721 0.02020 0.00902 -0.0037 1.0000 0.2868
-4.000 -0.4492 0.01946 0.00844 -0.0029 1.0000 0.3283
-3.750 -0.4270 0.01878 0.00790 -0.0018 1.0000 0.3742
-3.500 -0.4051 0.01815 0.00747 -0.0005 1.0000 0.4246
-3.250 -0.3837 0.01756 0.00711 0.0010 1.0000 0.4808
-3.000 -0.3628 0.01702 0.00683 0.0027 1.0000 0.5413
-2.750 -0.3421 0.01655 0.00659 0.0048 1.0000 0.6058
-2.500 -0.3211 0.01615 0.00644 0.0071 1.0000 0.6715
-2.250 -0.2982 0.01585 0.00633 0.0092 1.0000 0.7386
-2.000 -0.2693 0.01565 0.00625 0.0103 1.0000 0.8051
-1.750 -0.2292 0.01556 0.00613 0.0091 1.0000 0.8693
-1.500 -0.1768 0.01552 0.00598 0.0050 1.0000 0.9237
-1.250 -0.1191 0.01542 0.00572 -0.0007 1.0000 0.9677
-1.000 -0.0630 0.01522 0.00537 -0.0068 1.0000 1.0000
-0.750 -0.0478 0.01506 0.00516 -0.0051 1.0000 1.0000
-0.500 -0.0320 0.01495 0.00502 -0.0034 1.0000 1.0000
-0.250 -0.0160 0.01489 0.00493 -0.0017 1.0000 1.0000
0.000 0.0000 0.01487 0.00490 0.0000 1.0000 1.0000
0.250 0.0160 0.01489 0.00493 0.0017 1.0000 1.0000
0.500 0.0320 0.01495 0.00502 0.0034 1.0000 1.0000
0.750 0.0478 0.01506 0.00516 0.0051 1.0000 1.0000
1.000 0.0630 0.01522 0.00537 0.0068 1.0000 1.0000
1.250 0.1191 0.01542 0.00571 0.0007 0.9677 1.0000
1.500 0.1768 0.01551 0.00598 -0.0050 0.9236 1.0000
1.750 0.2291 0.01556 0.00613 -0.0090 0.8694 1.0000
2.000 0.2692 0.01565 0.00625 -0.0103 0.8053 1.0000
2.250 0.2981 0.01585 0.00633 -0.0092 0.7386 1.0000
2.500 0.3209 0.01615 0.00644 -0.0070 0.6716 1.0000
2.750 0.3420 0.01655 0.00659 -0.0048 0.6059 1.0000
3.000 0.3627 0.01702 0.00683 -0.0027 0.5414 1.0000
3.250 0.3836 0.01756 0.00711 -0.0009 0.4809 1.0000
3.500 0.4050 0.01815 0.00747 0.0006 0.4246 1.0000
3.750 0.4268 0.01878 0.00790 0.0018 0.3742 1.0000
4.000 0.4491 0.01946 0.00844 0.0029 0.3283 1.0000
4.250 0.4721 0.02020 0.00902 0.0038 0.2868 1.0000
4.500 0.4956 0.02099 0.00970 0.0045 0.2509 1.0000
4.750 0.5192 0.02184 0.01045 0.0051 0.2207 1.0000
5.000 0.5427 0.02272 0.01129 0.0058 0.1936 1.0000
5.250 0.5664 0.02372 0.01234 0.0066 0.1726 1.0000
5.500 0.5897 0.02474 0.01338 0.0074 0.1531 1.0000
5.750 0.6128 0.02586 0.01452 0.0082 0.1375 1.0000
6.000 0.6358 0.02707 0.01580 0.0089 0.1236 1.0000
6.250 0.6586 0.02834 0.01719 0.0097 0.1109 1.0000
6.500 0.6813 0.02992 0.01900 0.0105 0.1012 1.0000
6.750 0.7028 0.03132 0.02045 0.0113 0.0920 1.0000
7.000 0.7246 0.03329 0.02277 0.0121 0.0851 1.0000
7.250 0.7453 0.03518 0.02469 0.0128 0.0800 1.0000
7.500 0.7638 0.03762 0.02771 0.0137 0.0736 1.0000
7.750 0.7824 0.03951 0.02972 0.0144 0.0692 1.0000
8.000 0.7979 0.04262 0.03321 0.0151 0.0668 1.0000
8.250 0.8070 0.04685 0.03811 0.0158 0.0649 1.0000
8.500 0.8112 0.05132 0.04313 0.0162 0.0630 1.0000
8.750 0.8115 0.05573 0.04796 0.0162 0.0611 1.0000
9.000 0.8100 0.05984 0.05234 0.0160 0.0593 1.0000
9.250 0.8127 0.06291 0.05552 0.0160 0.0573 1.0000
9.500 0.8093 0.06669 0.05942 0.0155 0.0562 1.0000
9.750 0.7392 0.08148 0.07436 0.0045 0.0614 1.0000
10.000 0.7215 0.09072 0.08354 -0.0024 0.0623 1.0000
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Polar data table (+)
Polar graphs
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