S9027 (8%) (s9027-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9027 (8%) (s9027-il) Reynolds number: 200,000 Max Cl/Cd: 40.72 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9027-il-200000.txt Download as CSV file: xf-s9027-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.7551 0.08382 0.08031 -0.0008 1.0000 0.0426
-10.250 -0.7834 0.07184 0.06836 -0.0098 1.0000 0.0410
-10.000 -0.8191 0.06240 0.05881 -0.0182 1.0000 0.0396
-9.750 -0.8533 0.05605 0.05226 -0.0195 1.0000 0.0386
-9.500 -0.8833 0.04823 0.04395 -0.0197 1.0000 0.0374
-9.250 -0.8936 0.04224 0.03743 -0.0187 1.0000 0.0371
-9.000 -0.8895 0.03816 0.03291 -0.0175 1.0000 0.0377
-8.750 -0.8773 0.03551 0.02993 -0.0164 1.0000 0.0394
-8.500 -0.8638 0.03278 0.02677 -0.0152 1.0000 0.0411
-8.250 -0.8479 0.03009 0.02363 -0.0139 1.0000 0.0421
-8.000 -0.8289 0.02806 0.02120 -0.0128 1.0000 0.0432
-7.750 -0.8112 0.02497 0.01774 -0.0117 1.0000 0.0450
-7.500 -0.7895 0.02350 0.01624 -0.0110 1.0000 0.0478
-7.250 -0.7667 0.02217 0.01471 -0.0102 1.0000 0.0503
-7.000 -0.7434 0.02085 0.01320 -0.0093 1.0000 0.0531
-6.750 -0.7199 0.01953 0.01168 -0.0084 1.0000 0.0560
-6.500 -0.6975 0.01821 0.01041 -0.0076 1.0000 0.0612
-6.250 -0.6730 0.01760 0.00963 -0.0068 1.0000 0.0676
-6.000 -0.6507 0.01641 0.00852 -0.0059 1.0000 0.0760
-5.750 -0.6276 0.01552 0.00761 -0.0050 1.0000 0.0854
-5.500 -0.6038 0.01486 0.00695 -0.0042 1.0000 0.0972
-5.250 -0.5801 0.01425 0.00636 -0.0034 1.0000 0.1104
-5.000 -0.5564 0.01366 0.00583 -0.0027 1.0000 0.1258
-4.750 -0.5326 0.01313 0.00535 -0.0019 1.0000 0.1452
-4.500 -0.5091 0.01257 0.00490 -0.0011 1.0000 0.1683
-4.250 -0.4856 0.01204 0.00449 -0.0003 1.0000 0.1951
-4.000 -0.4621 0.01155 0.00414 0.0005 1.0000 0.2268
-3.750 -0.4387 0.01110 0.00382 0.0014 1.0000 0.2639
-3.500 -0.4155 0.01065 0.00356 0.0022 1.0000 0.3046
-3.250 -0.3924 0.01023 0.00333 0.0031 1.0000 0.3504
-3.000 -0.3696 0.00981 0.00315 0.0041 1.0000 0.4034
-2.750 -0.3471 0.00942 0.00299 0.0052 1.0000 0.4613
-2.500 -0.3251 0.00903 0.00288 0.0065 1.0000 0.5240
-2.250 -0.3036 0.00867 0.00281 0.0080 1.0000 0.5902
-2.000 -0.2824 0.00835 0.00277 0.0096 1.0000 0.6544
-1.750 -0.2619 0.00807 0.00276 0.0115 1.0000 0.7188
-1.500 -0.2417 0.00786 0.00279 0.0136 1.0000 0.7823
-1.250 -0.2204 0.00773 0.00288 0.0157 1.0000 0.8457
-1.000 -0.1856 0.00777 0.00304 0.0151 1.0000 0.9104
-0.750 -0.1316 0.00790 0.00316 0.0103 1.0000 0.9555
-0.500 -0.0765 0.00798 0.00321 0.0050 1.0000 0.9821
-0.250 -0.0165 0.00798 0.00318 -0.0016 1.0000 0.9980
0.000 0.0000 0.00794 0.00314 0.0000 1.0000 1.0000
0.250 0.0164 0.00798 0.00318 0.0016 0.9980 1.0000
0.500 0.0764 0.00798 0.00321 -0.0050 0.9821 1.0000
0.750 0.1314 0.00790 0.00316 -0.0103 0.9557 1.0000
1.000 0.1855 0.00777 0.00304 -0.0151 0.9106 1.0000
1.250 0.2202 0.00773 0.00288 -0.0156 0.8455 1.0000
1.500 0.2415 0.00786 0.00279 -0.0136 0.7825 1.0000
1.750 0.2616 0.00807 0.00276 -0.0114 0.7187 1.0000
2.000 0.2822 0.00835 0.00277 -0.0095 0.6546 1.0000
2.250 0.3033 0.00866 0.00281 -0.0079 0.5901 1.0000
2.500 0.3248 0.00903 0.00288 -0.0064 0.5240 1.0000
2.750 0.3468 0.00941 0.00299 -0.0052 0.4616 1.0000
3.000 0.3693 0.00981 0.00315 -0.0041 0.4035 1.0000
3.250 0.3921 0.01022 0.00333 -0.0031 0.3508 1.0000
3.500 0.4151 0.01065 0.00355 -0.0022 0.3048 1.0000
3.750 0.4384 0.01109 0.00382 -0.0013 0.2641 1.0000
4.000 0.4618 0.01155 0.00414 -0.0005 0.2271 1.0000
4.250 0.4853 0.01204 0.00448 0.0003 0.1952 1.0000
4.500 0.5088 0.01257 0.00490 0.0012 0.1684 1.0000
4.750 0.5324 0.01313 0.00534 0.0020 0.1452 1.0000
5.000 0.5562 0.01366 0.00583 0.0027 0.1260 1.0000
5.250 0.5799 0.01425 0.00636 0.0035 0.1105 1.0000
5.500 0.6037 0.01486 0.00695 0.0042 0.0973 1.0000
5.750 0.6275 0.01552 0.00761 0.0050 0.0854 1.0000
6.000 0.6507 0.01641 0.00852 0.0059 0.0759 1.0000
6.250 0.6730 0.01761 0.00964 0.0068 0.0676 1.0000
6.500 0.6976 0.01821 0.01040 0.0076 0.0612 1.0000
6.750 0.7199 0.01958 0.01173 0.0084 0.0559 1.0000
7.000 0.7435 0.02086 0.01321 0.0093 0.0531 1.0000
7.250 0.7670 0.02217 0.01472 0.0102 0.0503 1.0000
7.500 0.7898 0.02348 0.01622 0.0110 0.0477 1.0000
7.750 0.8115 0.02496 0.01774 0.0117 0.0450 1.0000
8.000 0.8293 0.02806 0.02119 0.0127 0.0431 1.0000
8.250 0.8483 0.03012 0.02366 0.0139 0.0421 1.0000
8.500 0.8642 0.03283 0.02682 0.0151 0.0411 1.0000
8.750 0.8777 0.03559 0.03001 0.0163 0.0394 1.0000
9.000 0.8904 0.03811 0.03285 0.0174 0.0376 1.0000
9.250 0.8943 0.04225 0.03744 0.0185 0.0371 1.0000
9.500 0.8836 0.04834 0.04407 0.0195 0.0374 1.0000
9.750 0.8538 0.05617 0.05237 0.0193 0.0386 1.0000
10.000 0.8196 0.06255 0.05897 0.0179 0.0397 1.0000
10.250 0.7830 0.07234 0.06887 0.0090 0.0410 1.0000
10.500 0.7506 0.08737 0.08388 -0.0017 0.0454 1.0000
10.750 0.7558 0.08892 0.08543 -0.0012 0.0443 1.0000
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Polar data table (+)
Polar graphs
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