S9032 (9%) (s9032-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9032 (9%) (s9032-il) Reynolds number: 100,000 Max Cl/Cd: 32.74 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9032-il-100000.txt Download as CSV file: xf-s9032-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S9032 (9%)
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.7379 0.08392 0.07899 -0.0071 1.0000 0.0901
-9.750 -0.7529 0.07538 0.07045 -0.0125 1.0000 0.0842
-9.500 -0.8555 0.06105 0.05541 -0.0199 1.0000 0.0748
-9.250 -0.8579 0.05567 0.04983 -0.0196 1.0000 0.0742
-9.000 -0.8591 0.05062 0.04445 -0.0190 1.0000 0.0736
-8.750 -0.8575 0.04590 0.03928 -0.0180 1.0000 0.0734
-8.500 -0.8514 0.04166 0.03450 -0.0167 1.0000 0.0738
-8.250 -0.8410 0.03816 0.03039 -0.0152 1.0000 0.0747
-8.000 -0.8256 0.03489 0.02696 -0.0144 1.0000 0.0779
-7.750 -0.8055 0.03308 0.02504 -0.0136 1.0000 0.0821
-7.500 -0.7867 0.03060 0.02208 -0.0123 1.0000 0.0858
-7.250 -0.7662 0.02806 0.01914 -0.0112 1.0000 0.0899
-7.000 -0.7437 0.02648 0.01751 -0.0104 1.0000 0.0967
-6.750 -0.7215 0.02488 0.01578 -0.0095 1.0000 0.1058
-6.500 -0.6985 0.02349 0.01415 -0.0085 1.0000 0.1163
-6.250 -0.6756 0.02239 0.01299 -0.0076 1.0000 0.1294
-6.000 -0.6525 0.02120 0.01183 -0.0068 1.0000 0.1437
-5.750 -0.6296 0.02013 0.01086 -0.0060 1.0000 0.1602
-5.500 -0.6067 0.01917 0.00999 -0.0051 1.0000 0.1792
-5.250 -0.5840 0.01825 0.00913 -0.0041 1.0000 0.2025
-5.000 -0.5613 0.01738 0.00835 -0.0031 1.0000 0.2292
-4.750 -0.5392 0.01655 0.00772 -0.0020 1.0000 0.2600
-4.500 -0.5173 0.01583 0.00716 -0.0009 1.0000 0.2971
-4.250 -0.4957 0.01515 0.00670 0.0003 1.0000 0.3378
-4.000 -0.4742 0.01455 0.00632 0.0016 1.0000 0.3829
-3.750 -0.4529 0.01401 0.00600 0.0030 1.0000 0.4319
-3.500 -0.4319 0.01352 0.00575 0.0046 1.0000 0.4812
-3.250 -0.4110 0.01310 0.00554 0.0063 1.0000 0.5328
-3.000 -0.3903 0.01272 0.00540 0.0081 1.0000 0.5824
-2.750 -0.3697 0.01240 0.00527 0.0100 1.0000 0.6334
-2.500 -0.3495 0.01212 0.00518 0.0122 1.0000 0.6823
-2.250 -0.3298 0.01189 0.00514 0.0146 1.0000 0.7320
-2.000 -0.3100 0.01171 0.00512 0.0172 1.0000 0.7819
-1.750 -0.2881 0.01162 0.00517 0.0195 1.0000 0.8315
-1.500 -0.2593 0.01165 0.00526 0.0205 1.0000 0.8814
-1.250 -0.2108 0.01186 0.00543 0.0175 1.0000 0.9251
-1.000 -0.1442 0.01210 0.00556 0.0106 1.0000 0.9568
-0.750 -0.0690 0.01215 0.00550 0.0015 1.0000 0.9810
-0.500 0.0037 0.01193 0.00520 -0.0078 1.0000 1.0000
-0.250 0.0028 0.01167 0.00498 -0.0042 1.0000 1.0000
0.000 0.0000 0.01158 0.00490 0.0000 1.0000 1.0000
0.250 -0.0028 0.01167 0.00498 0.0042 1.0000 1.0000
0.500 -0.0037 0.01193 0.00520 0.0078 1.0000 1.0000
0.750 0.0690 0.01215 0.00550 -0.0015 0.9810 1.0000
1.000 0.1443 0.01210 0.00556 -0.0106 0.9567 1.0000
1.250 0.2109 0.01186 0.00543 -0.0175 0.9249 1.0000
1.500 0.2595 0.01165 0.00526 -0.0205 0.8814 1.0000
1.750 0.2883 0.01162 0.00517 -0.0195 0.8314 1.0000
2.000 0.3103 0.01171 0.00513 -0.0172 0.7818 1.0000
2.250 0.3301 0.01189 0.00514 -0.0147 0.7320 1.0000
2.500 0.3498 0.01212 0.00518 -0.0123 0.6822 1.0000
2.750 0.3700 0.01240 0.00527 -0.0101 0.6331 1.0000
3.000 0.3906 0.01272 0.00540 -0.0082 0.5822 1.0000
3.250 0.4114 0.01310 0.00554 -0.0063 0.5327 1.0000
3.500 0.4323 0.01352 0.00575 -0.0047 0.4810 1.0000
3.750 0.4533 0.01401 0.00601 -0.0031 0.4316 1.0000
4.000 0.4745 0.01455 0.00632 -0.0017 0.3827 1.0000
4.250 0.4960 0.01515 0.00671 -0.0004 0.3375 1.0000
4.500 0.5176 0.01583 0.00717 0.0008 0.2969 1.0000
4.750 0.5395 0.01655 0.00772 0.0020 0.2599 1.0000
5.000 0.5615 0.01738 0.00836 0.0030 0.2291 1.0000
5.250 0.5842 0.01826 0.00914 0.0041 0.2024 1.0000
5.500 0.6069 0.01917 0.00999 0.0050 0.1792 1.0000
5.750 0.6297 0.02013 0.01086 0.0059 0.1602 1.0000
6.000 0.6525 0.02121 0.01184 0.0068 0.1437 1.0000
6.250 0.6756 0.02240 0.01300 0.0076 0.1294 1.0000
6.500 0.6984 0.02348 0.01414 0.0085 0.1163 1.0000
6.750 0.7214 0.02487 0.01577 0.0095 0.1058 1.0000
7.000 0.7436 0.02649 0.01752 0.0104 0.0967 1.0000
7.250 0.7661 0.02805 0.01914 0.0112 0.0899 1.0000
7.500 0.7865 0.03059 0.02207 0.0124 0.0858 1.0000
7.750 0.8052 0.03308 0.02504 0.0137 0.0822 1.0000
8.000 0.8252 0.03490 0.02697 0.0145 0.0779 1.0000
8.250 0.8407 0.03815 0.03037 0.0153 0.0748 1.0000
8.500 0.8510 0.04161 0.03446 0.0168 0.0738 1.0000
8.750 0.8569 0.04586 0.03924 0.0181 0.0734 1.0000
9.000 0.8587 0.05055 0.04437 0.0191 0.0736 1.0000
9.250 0.8569 0.05562 0.04978 0.0198 0.0741 1.0000
9.500 0.8553 0.06097 0.05532 0.0200 0.0748 1.0000
9.750 0.6296 0.07871 0.07396 0.0047 0.0930 1.0000
10.000 0.6419 0.08048 0.07577 0.0061 0.0902 1.0000
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Polar data table (+)
Polar graphs
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