S9037 (9%) (s9037-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9037 (9%) (s9037-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.2 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9037-il-1000000.txt Download as CSV file: xf-s9037-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2622 0.08282 0.08135 -0.0346 1.0000 0.0093
-8.750 -0.2647 0.07858 0.07714 -0.0358 1.0000 0.0098
-8.500 -0.2662 0.07502 0.07360 -0.0362 0.9997 0.0099
-8.250 -0.2594 0.06995 0.06854 -0.0397 0.9960 0.0099
-8.000 -0.2528 0.06489 0.06348 -0.0434 0.9906 0.0100
-7.750 -0.2449 0.05949 0.05808 -0.0479 0.9862 0.0100
-7.500 -0.2366 0.05382 0.05241 -0.0533 0.9790 0.0100
-7.250 -0.2470 0.04523 0.04381 -0.0619 0.9594 0.0103
-7.000 -0.2480 0.03980 0.03831 -0.0673 0.9417 0.0104
-6.750 -0.2454 0.03515 0.03358 -0.0707 0.9276 0.0105
-6.500 -0.2379 0.03102 0.02933 -0.0733 0.9159 0.0107
-6.250 -0.2282 0.02642 0.02459 -0.0758 0.9054 0.0109
-6.000 -0.2149 0.02265 0.02066 -0.0773 0.8963 0.0113
-5.750 -0.2000 0.01875 0.01655 -0.0786 0.8873 0.0117
-5.500 -0.1826 0.01487 0.01241 -0.0795 0.8790 0.0126
-5.250 -0.1613 0.01184 0.00904 -0.0796 0.8717 0.0137
-5.000 -0.1371 0.01048 0.00734 -0.0794 0.8634 0.0142
-4.250 -0.0657 0.01259 0.00787 -0.0833 0.8582 0.0092
-4.000 -0.0403 0.01042 0.00535 -0.0824 0.8495 0.0078
-3.750 -0.0139 0.00955 0.00430 -0.0819 0.8408 0.0074
-3.500 0.0130 0.00900 0.00365 -0.0815 0.8313 0.0073
-3.250 0.0401 0.00852 0.00306 -0.0812 0.8217 0.0073
-3.000 0.0674 0.00813 0.00257 -0.0809 0.8124 0.0074
-2.750 0.0949 0.00782 0.00217 -0.0807 0.8024 0.0078
-2.500 0.1226 0.00758 0.00187 -0.0805 0.7924 0.0086
-2.250 0.1504 0.00733 0.00154 -0.0803 0.7825 0.0140
-2.000 0.1775 0.00699 0.00134 -0.0801 0.7721 0.0562
-1.750 0.2051 0.00679 0.00124 -0.0801 0.7606 0.0942
-1.500 0.2323 0.00654 0.00115 -0.0800 0.7486 0.1578
-1.250 0.2591 0.00621 0.00109 -0.0799 0.7362 0.2600
-1.000 0.2860 0.00593 0.00105 -0.0799 0.7238 0.3585
-0.750 0.3130 0.00569 0.00102 -0.0798 0.7115 0.4545
-0.500 0.3392 0.00536 0.00102 -0.0796 0.6990 0.5896
-0.250 0.3648 0.00507 0.00104 -0.0791 0.6864 0.7159
0.000 0.3876 0.00475 0.00108 -0.0778 0.6739 0.8549
0.250 0.4132 0.00461 0.00110 -0.0767 0.6608 0.9658
0.500 0.4569 0.00466 0.00106 -0.0802 0.6457 0.9982
0.750 0.4847 0.00476 0.00106 -0.0801 0.6296 1.0000
1.000 0.5109 0.00486 0.00108 -0.0797 0.6128 1.0000
1.250 0.5373 0.00497 0.00110 -0.0794 0.5967 1.0000
1.500 0.5639 0.00508 0.00113 -0.0791 0.5806 1.0000
1.750 0.5905 0.00520 0.00117 -0.0788 0.5651 1.0000
2.000 0.6171 0.00534 0.00123 -0.0785 0.5481 1.0000
2.250 0.6435 0.00549 0.00129 -0.0783 0.5291 1.0000
2.500 0.6701 0.00565 0.00136 -0.0780 0.5087 1.0000
3.000 0.7230 0.00599 0.00154 -0.0775 0.4701 1.0000
3.250 0.7496 0.00616 0.00163 -0.0773 0.4518 1.0000
3.500 0.7759 0.00635 0.00174 -0.0770 0.4331 1.0000
3.750 0.8023 0.00654 0.00186 -0.0768 0.4153 1.0000
4.000 0.8288 0.00673 0.00198 -0.0766 0.3985 1.0000
4.250 0.8550 0.00694 0.00213 -0.0763 0.3786 1.0000
4.500 0.8807 0.00720 0.00228 -0.0760 0.3557 1.0000
4.750 0.9066 0.00744 0.00245 -0.0757 0.3351 1.0000
5.000 0.9324 0.00769 0.00263 -0.0754 0.3179 1.0000
5.250 0.9583 0.00792 0.00281 -0.0752 0.2996 1.0000
5.500 0.9837 0.00821 0.00301 -0.0748 0.2789 1.0000
5.750 1.0091 0.00849 0.00322 -0.0745 0.2613 1.0000
6.000 1.0345 0.00876 0.00345 -0.0742 0.2447 1.0000
6.250 1.0592 0.00911 0.00370 -0.0738 0.2228 1.0000
6.500 1.0835 0.00948 0.00398 -0.0733 0.2001 1.0000
6.750 1.1077 0.00986 0.00427 -0.0728 0.1804 1.0000
7.000 1.1319 0.01023 0.00458 -0.0724 0.1631 1.0000
7.250 1.1558 0.01061 0.00490 -0.0719 0.1456 1.0000
7.500 1.1790 0.01107 0.00525 -0.0712 0.1266 1.0000
7.750 1.2022 0.01150 0.00562 -0.0706 0.1113 1.0000
8.000 1.2254 0.01192 0.00599 -0.0700 0.0982 1.0000
8.250 1.2482 0.01237 0.00640 -0.0694 0.0852 1.0000
8.500 1.2703 0.01287 0.00683 -0.0687 0.0712 1.0000
8.750 1.2920 0.01338 0.00729 -0.0679 0.0597 1.0000
9.000 1.3134 0.01390 0.00777 -0.0670 0.0500 1.0000
9.250 1.3340 0.01447 0.00829 -0.0661 0.0401 1.0000
9.500 1.3542 0.01505 0.00883 -0.0651 0.0320 1.0000
9.750 1.3747 0.01558 0.00937 -0.0641 0.0267 1.0000
10.000 1.3939 0.01618 0.00996 -0.0630 0.0212 1.0000
10.250 1.4113 0.01689 0.01065 -0.0616 0.0147 1.0000
10.500 1.4242 0.01792 0.01162 -0.0596 0.0068 1.0000
10.750 1.4375 0.01885 0.01259 -0.0575 0.0048 1.0000
11.000 1.4518 0.01950 0.01331 -0.0555 0.0044 1.0000
11.250 1.4634 0.02021 0.01410 -0.0532 0.0040 1.0000
11.500 1.4741 0.02099 0.01495 -0.0508 0.0037 1.0000
11.750 1.4830 0.02190 0.01595 -0.0483 0.0035 1.0000
12.000 1.4851 0.02331 0.01749 -0.0451 0.0030 1.0000
12.250 1.4898 0.02459 0.01889 -0.0426 0.0030 1.0000
12.500 1.4957 0.02584 0.02024 -0.0404 0.0029 1.0000
12.750 1.5013 0.02717 0.02168 -0.0384 0.0028 1.0000
13.000 1.5052 0.02872 0.02333 -0.0364 0.0027 1.0000
13.250 1.5081 0.03042 0.02515 -0.0346 0.0027 1.0000
13.500 1.5088 0.03242 0.02726 -0.0330 0.0026 1.0000
13.750 1.5079 0.03469 0.02965 -0.0316 0.0025 1.0000
14.000 1.5091 0.03689 0.03195 -0.0306 0.0024 1.0000
14.250 1.5052 0.03975 0.03495 -0.0298 0.0024 1.0000
14.500 1.5036 0.04253 0.03784 -0.0294 0.0024 1.0000
14.750 1.4986 0.04589 0.04132 -0.0293 0.0023 1.0000
15.000 1.4938 0.04941 0.04497 -0.0296 0.0022 1.0000
15.250 1.4894 0.05306 0.04874 -0.0302 0.0022 1.0000
15.500 1.4804 0.05758 0.05339 -0.0313 0.0021 1.0000
15.750 1.4707 0.06247 0.05843 -0.0329 0.0022 1.0000
16.000 1.4554 0.06852 0.06463 -0.0351 0.0021 1.0000
16.250 1.4464 0.07382 0.07004 -0.0373 0.0021 1.0000
16.500 1.4327 0.08017 0.07653 -0.0402 0.0021 1.0000
16.750 1.4168 0.08716 0.08366 -0.0435 0.0021 1.0000
17.000 1.4004 0.09451 0.09116 -0.0471 0.0021 1.0000
17.250 1.3832 0.10219 0.09897 -0.0510 0.0021 1.0000
17.500 1.3691 0.10949 0.10640 -0.0548 0.0021 1.0000
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Polar data table (+)
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