S9027 (8%) (s9027-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9027 (8%) (s9027-il) Reynolds number: 100,000 Max Cl/Cd: 30.64 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9027-il-100000.txt Download as CSV file: xf-s9027-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.7039 0.10193 0.09703 0.0072 1.0000 0.1488
-9.250 -0.6720 0.09736 0.09236 0.0120 1.0000 0.1514
-9.000 -0.7887 0.06659 0.06148 -0.0151 1.0000 0.0794
-8.750 -0.7941 0.06107 0.05581 -0.0159 1.0000 0.0786
-8.500 -0.7991 0.05538 0.04984 -0.0164 1.0000 0.0778
-8.250 -0.8007 0.04973 0.04377 -0.0164 1.0000 0.0769
-8.000 -0.7972 0.04436 0.03791 -0.0159 1.0000 0.0760
-7.750 -0.7888 0.03958 0.03257 -0.0149 1.0000 0.0758
-7.500 -0.7757 0.03562 0.02803 -0.0138 1.0000 0.0768
-7.250 -0.7589 0.03248 0.02425 -0.0125 1.0000 0.0791
-7.000 -0.7397 0.02988 0.02138 -0.0116 1.0000 0.0836
-6.750 -0.7174 0.02811 0.01944 -0.0108 1.0000 0.0889
-6.500 -0.6947 0.02612 0.01688 -0.0095 1.0000 0.0941
-6.250 -0.6715 0.02427 0.01512 -0.0089 1.0000 0.1022
-6.000 -0.6482 0.02285 0.01359 -0.0081 1.0000 0.1131
-5.750 -0.6242 0.02145 0.01209 -0.0072 1.0000 0.1249
-5.500 -0.6006 0.02043 0.01108 -0.0064 1.0000 0.1403
-5.250 -0.5768 0.01941 0.01007 -0.0056 1.0000 0.1573
-5.000 -0.5531 0.01847 0.00910 -0.0048 1.0000 0.1780
-4.750 -0.5297 0.01750 0.00827 -0.0039 1.0000 0.2008
-4.500 -0.5065 0.01665 0.00755 -0.0030 1.0000 0.2300
-4.250 -0.4835 0.01581 0.00686 -0.0020 1.0000 0.2638
-4.000 -0.4610 0.01505 0.00632 -0.0009 1.0000 0.3051
-3.750 -0.4390 0.01432 0.00586 0.0002 1.0000 0.3524
-3.500 -0.4173 0.01365 0.00549 0.0015 1.0000 0.4088
-3.250 -0.3963 0.01302 0.00520 0.0031 1.0000 0.4725
-3.000 -0.3757 0.01245 0.00498 0.0049 1.0000 0.5428
-2.750 -0.3556 0.01196 0.00481 0.0070 1.0000 0.6165
-2.500 -0.3356 0.01156 0.00472 0.0094 1.0000 0.6911
-2.250 -0.3151 0.01128 0.00470 0.0121 1.0000 0.7655
-2.000 -0.2915 0.01114 0.00474 0.0144 1.0000 0.8373
-1.750 -0.2499 0.01124 0.00485 0.0134 1.0000 0.9039
-1.500 -0.1857 0.01147 0.00493 0.0073 1.0000 0.9525
-1.250 -0.1066 0.01153 0.00479 -0.0026 1.0000 0.9838
-1.000 -0.0512 0.01127 0.00441 -0.0088 1.0000 1.0000
-0.750 -0.0395 0.01104 0.00416 -0.0067 1.0000 1.0000
-0.500 -0.0270 0.01089 0.00399 -0.0044 1.0000 1.0000
-0.250 -0.0139 0.01081 0.00390 -0.0022 1.0000 1.0000
0.000 0.0000 0.01078 0.00387 0.0000 1.0000 1.0000
0.250 0.0139 0.01081 0.00390 0.0022 1.0000 1.0000
0.500 0.0270 0.01089 0.00399 0.0044 1.0000 1.0000
0.750 0.0395 0.01104 0.00416 0.0066 1.0000 1.0000
1.000 0.0512 0.01127 0.00441 0.0088 1.0000 1.0000
1.250 0.1064 0.01153 0.00478 0.0026 0.9839 1.0000
1.500 0.1855 0.01147 0.00492 -0.0072 0.9526 1.0000
1.750 0.2499 0.01124 0.00484 -0.0134 0.9037 1.0000
2.000 0.2913 0.01114 0.00473 -0.0144 0.8372 1.0000
2.250 0.3148 0.01128 0.00469 -0.0120 0.7656 1.0000
2.500 0.3353 0.01156 0.00472 -0.0094 0.6913 1.0000
2.750 0.3553 0.01196 0.00481 -0.0070 0.6167 1.0000
3.000 0.3755 0.01245 0.00498 -0.0048 0.5430 1.0000
3.250 0.3960 0.01302 0.00519 -0.0030 0.4729 1.0000
3.500 0.4171 0.01365 0.00548 -0.0015 0.4089 1.0000
3.750 0.4388 0.01432 0.00586 -0.0002 0.3526 1.0000
4.000 0.4607 0.01505 0.00631 0.0010 0.3053 1.0000
4.250 0.4833 0.01581 0.00686 0.0020 0.2639 1.0000
4.500 0.5064 0.01665 0.00755 0.0030 0.2300 1.0000
4.750 0.5295 0.01750 0.00826 0.0039 0.2008 1.0000
5.000 0.5529 0.01847 0.00910 0.0048 0.1781 1.0000
5.250 0.5767 0.01940 0.01006 0.0056 0.1572 1.0000
5.500 0.6006 0.02042 0.01107 0.0065 0.1403 1.0000
5.750 0.6241 0.02145 0.01209 0.0072 0.1249 1.0000
6.000 0.6482 0.02286 0.01359 0.0081 0.1131 1.0000
6.250 0.6716 0.02427 0.01513 0.0089 0.1022 1.0000
6.500 0.6948 0.02614 0.01690 0.0095 0.0940 1.0000
6.750 0.7175 0.02811 0.01944 0.0107 0.0888 1.0000
7.000 0.7398 0.02991 0.02141 0.0116 0.0837 1.0000
7.250 0.7591 0.03249 0.02426 0.0124 0.0791 1.0000
7.500 0.7760 0.03564 0.02805 0.0137 0.0768 1.0000
7.750 0.7892 0.03960 0.03260 0.0149 0.0758 1.0000
8.000 0.7975 0.04440 0.03795 0.0158 0.0760 1.0000
8.250 0.8010 0.04980 0.04384 0.0163 0.0769 1.0000
8.500 0.7994 0.05546 0.04993 0.0163 0.0777 1.0000
8.750 0.7946 0.06114 0.05588 0.0157 0.0786 1.0000
9.000 0.7892 0.06668 0.06157 0.0149 0.0794 1.0000
9.250 0.6736 0.09744 0.09246 -0.0122 0.1513 1.0000
9.500 0.7065 0.10200 0.09711 -0.0072 0.1489 1.0000
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Polar data table (+)
Polar graphs
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