S9037 (9%) (s9037-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9037 (9%) (s9037-il) Reynolds number: 500,000 Max Cl/Cd: 95.16 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9037-il-500000-n5.txt Download as CSV file: xf-s9037-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S9037 (9%)
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3469 0.09696 0.09467 -0.0322 1.0000 0.0099
-9.000 -0.3444 0.09356 0.09129 -0.0333 1.0000 0.0099
-8.000 -0.3518 0.07945 0.07735 -0.0367 0.9991 0.0102
-7.750 -0.3371 0.07736 0.07527 -0.0391 0.9901 0.0108
-7.500 -0.3206 0.07286 0.07077 -0.0455 0.9816 0.0110
-7.250 -0.2378 0.04941 0.04736 -0.0575 0.9425 0.0095
-7.000 -0.2391 0.04517 0.04309 -0.0612 0.9261 0.0092
-6.750 -0.2388 0.03992 0.03777 -0.0660 0.9124 0.0088
-6.500 -0.2562 0.03887 0.03622 -0.0831 0.9238 0.0067
-6.250 -0.2452 0.03261 0.02960 -0.0850 0.9120 0.0065
-6.000 -0.2323 0.02641 0.02288 -0.0856 0.9013 0.0062
-5.750 -0.2150 0.02180 0.01770 -0.0854 0.8920 0.0060
-5.500 -0.1940 0.01857 0.01391 -0.0848 0.8840 0.0059
-5.250 -0.1704 0.01638 0.01128 -0.0842 0.8756 0.0057
-5.000 -0.1456 0.01477 0.00932 -0.0836 0.8677 0.0057
-4.750 -0.1202 0.01357 0.00786 -0.0831 0.8591 0.0057
-4.500 -0.0943 0.01263 0.00670 -0.0826 0.8501 0.0058
-4.250 -0.0682 0.01188 0.00579 -0.0821 0.8411 0.0058
-4.000 -0.0419 0.01124 0.00501 -0.0817 0.8315 0.0059
-3.750 -0.0152 0.01070 0.00435 -0.0814 0.8222 0.0061
-3.500 0.0116 0.01026 0.00380 -0.0811 0.8129 0.0064
-3.250 0.0387 0.00991 0.00332 -0.0808 0.8028 0.0067
-3.000 0.0658 0.00955 0.00287 -0.0805 0.7924 0.0074
-2.750 0.0931 0.00931 0.00254 -0.0802 0.7815 0.0089
-2.500 0.1203 0.00907 0.00225 -0.0800 0.7703 0.0127
-2.250 0.1475 0.00884 0.00202 -0.0797 0.7587 0.0274
-2.000 0.1745 0.00857 0.00185 -0.0796 0.7470 0.0607
-1.750 0.2015 0.00829 0.00172 -0.0795 0.7353 0.1134
-1.500 0.2285 0.00808 0.00161 -0.0794 0.7239 0.1635
-1.250 0.2555 0.00788 0.00152 -0.0792 0.7121 0.2225
-1.000 0.2825 0.00769 0.00146 -0.0791 0.6997 0.2875
-0.750 0.3092 0.00749 0.00141 -0.0790 0.6860 0.3657
-0.500 0.3357 0.00730 0.00138 -0.0788 0.6717 0.4448
-0.250 0.3617 0.00703 0.00138 -0.0785 0.6575 0.5572
0.000 0.3867 0.00675 0.00140 -0.0779 0.6435 0.6768
0.250 0.4092 0.00645 0.00144 -0.0765 0.6296 0.8058
0.500 0.4320 0.00628 0.00147 -0.0748 0.6159 0.9251
0.750 0.4744 0.00632 0.00143 -0.0778 0.5998 0.9914
1.000 0.5038 0.00642 0.00144 -0.0782 0.5845 1.0000
1.250 0.5299 0.00655 0.00147 -0.0778 0.5678 1.0000
1.500 0.5559 0.00670 0.00151 -0.0774 0.5488 1.0000
1.750 0.5819 0.00687 0.00156 -0.0770 0.5296 1.0000
2.000 0.6081 0.00703 0.00162 -0.0767 0.5118 1.0000
2.250 0.6344 0.00719 0.00170 -0.0764 0.4948 1.0000
2.500 0.6606 0.00736 0.00179 -0.0761 0.4781 1.0000
2.750 0.6867 0.00754 0.00188 -0.0757 0.4607 1.0000
3.000 0.7125 0.00775 0.00200 -0.0754 0.4400 1.0000
3.250 0.7382 0.00798 0.00214 -0.0750 0.4189 1.0000
3.500 0.7641 0.00820 0.00227 -0.0747 0.4000 1.0000
3.750 0.7900 0.00841 0.00241 -0.0744 0.3828 1.0000
4.000 0.8158 0.00864 0.00257 -0.0741 0.3659 1.0000
4.250 0.8414 0.00888 0.00276 -0.0737 0.3483 1.0000
4.750 0.8926 0.00938 0.00314 -0.0731 0.3154 1.0000
5.000 0.9176 0.00968 0.00336 -0.0727 0.2940 1.0000
5.250 0.9423 0.01001 0.00361 -0.0722 0.2725 1.0000
5.500 0.9672 0.01032 0.00386 -0.0718 0.2536 1.0000
5.750 0.9921 0.01063 0.00412 -0.0714 0.2383 1.0000
6.000 1.0164 0.01098 0.00442 -0.0709 0.2209 1.0000
6.250 1.0407 0.01133 0.00472 -0.0705 0.2030 1.0000
6.500 1.0650 0.01168 0.00503 -0.0700 0.1884 1.0000
6.750 1.0887 0.01207 0.00537 -0.0695 0.1715 1.0000
7.000 1.1115 0.01255 0.00576 -0.0688 0.1521 1.0000
7.250 1.1346 0.01298 0.00616 -0.0682 0.1361 1.0000
7.500 1.1574 0.01343 0.00657 -0.0675 0.1215 1.0000
7.750 1.1801 0.01388 0.00699 -0.0669 0.1100 1.0000
8.000 1.2024 0.01435 0.00744 -0.0661 0.0988 1.0000
8.250 1.2240 0.01486 0.00792 -0.0653 0.0859 1.0000
8.500 1.2447 0.01544 0.00846 -0.0644 0.0714 1.0000
8.750 1.2651 0.01603 0.00901 -0.0635 0.0606 1.0000
9.000 1.2847 0.01665 0.00961 -0.0624 0.0504 1.0000
9.250 1.3036 0.01731 0.01023 -0.0613 0.0406 1.0000
9.500 1.3226 0.01792 0.01085 -0.0601 0.0336 1.0000
9.750 1.3405 0.01859 0.01152 -0.0588 0.0276 1.0000
10.000 1.3572 0.01930 0.01226 -0.0574 0.0228 1.0000
10.250 1.3742 0.01994 0.01295 -0.0560 0.0195 1.0000
10.500 1.3870 0.02071 0.01374 -0.0539 0.0157 1.0000
10.750 1.3994 0.02146 0.01454 -0.0518 0.0123 1.0000
11.000 1.4092 0.02237 0.01548 -0.0495 0.0089 1.0000
11.250 1.4170 0.02344 0.01658 -0.0470 0.0061 1.0000
11.500 1.4249 0.02454 0.01774 -0.0447 0.0049 1.0000
11.750 1.4334 0.02562 0.01893 -0.0427 0.0042 1.0000
12.000 1.4407 0.02685 0.02025 -0.0406 0.0037 1.0000
12.250 1.4473 0.02817 0.02170 -0.0387 0.0034 1.0000
12.500 1.4528 0.02963 0.02327 -0.0369 0.0032 1.0000
12.750 1.4555 0.03141 0.02517 -0.0352 0.0030 1.0000
13.000 1.4591 0.03320 0.02709 -0.0337 0.0029 1.0000
13.250 1.4626 0.03507 0.02909 -0.0325 0.0028 1.0000
13.500 1.4643 0.03722 0.03137 -0.0314 0.0027 1.0000
13.750 1.4645 0.03964 0.03393 -0.0306 0.0026 1.0000
14.000 1.4643 0.04223 0.03666 -0.0300 0.0025 1.0000
14.250 1.4616 0.04524 0.03980 -0.0297 0.0024 1.0000
14.500 1.4581 0.04851 0.04322 -0.0298 0.0024 1.0000
14.750 1.4532 0.05214 0.04699 -0.0302 0.0023 1.0000
15.000 1.4464 0.05620 0.05121 -0.0310 0.0023 1.0000
15.250 1.4390 0.06060 0.05575 -0.0322 0.0023 1.0000
15.500 1.4301 0.06542 0.06073 -0.0338 0.0022 1.0000
15.750 1.4192 0.07085 0.06631 -0.0358 0.0022 1.0000
16.000 1.4071 0.07673 0.07234 -0.0383 0.0021 1.0000
16.250 1.3942 0.08295 0.07872 -0.0411 0.0021 1.0000
16.500 1.3803 0.08965 0.08559 -0.0443 0.0021 1.0000
16.750 1.3653 0.09677 0.09286 -0.0478 0.0021 1.0000
17.000 1.3491 0.10431 0.10055 -0.0516 0.0021 1.0000
17.250 1.3327 0.11211 0.10849 -0.0557 0.0021 1.0000
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Polar data table (+)
Polar graphs
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