SD8020-010-88 (sd8020-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD8020-010-88 (sd8020-il) Reynolds number: 50,000 Max Cl/Cd: 26.6 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd8020-il-50000-n5.txt Download as CSV file: xf-sd8020-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD8020-010-88
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.7519 0.08448 0.07720 -0.0238 1.0000 0.0531
-11.250 -0.7731 0.07740 0.07007 -0.0284 1.0000 0.0527
-11.000 -0.7957 0.07133 0.06391 -0.0317 1.0000 0.0524
-10.750 -0.8180 0.06633 0.05875 -0.0331 1.0000 0.0522
-10.500 -0.8388 0.06219 0.05442 -0.0325 1.0000 0.0523
-10.250 -0.8577 0.05839 0.05033 -0.0306 1.0000 0.0527
-10.000 -0.8702 0.05453 0.04606 -0.0287 1.0000 0.0533
-9.750 -0.8662 0.05160 0.04307 -0.0273 1.0000 0.0548
-9.500 -0.8616 0.04880 0.04008 -0.0257 1.0000 0.0565
-9.250 -0.8556 0.04596 0.03692 -0.0240 1.0000 0.0586
-9.000 -0.8481 0.04319 0.03375 -0.0222 1.0000 0.0620
-8.750 -0.8382 0.04059 0.03076 -0.0205 1.0000 0.0664
-8.500 -0.8239 0.03884 0.02897 -0.0191 1.0000 0.0712
-8.250 -0.8081 0.03647 0.02617 -0.0176 1.0000 0.0769
-8.000 -0.7921 0.03480 0.02450 -0.0162 1.0000 0.0836
-7.750 -0.7754 0.03310 0.02259 -0.0147 1.0000 0.0932
-7.500 -0.7579 0.03162 0.02090 -0.0132 1.0000 0.1045
-7.250 -0.7408 0.03029 0.01948 -0.0118 1.0000 0.1174
-7.000 -0.7233 0.02905 0.01821 -0.0103 1.0000 0.1324
-6.750 -0.7053 0.02787 0.01705 -0.0089 1.0000 0.1483
-6.500 -0.6873 0.02679 0.01598 -0.0074 1.0000 0.1669
-6.250 -0.6681 0.02576 0.01487 -0.0060 1.0000 0.1879
-6.000 -0.6498 0.02480 0.01400 -0.0045 1.0000 0.2102
-5.750 -0.6309 0.02390 0.01310 -0.0031 1.0000 0.2355
-5.500 -0.6121 0.02307 0.01233 -0.0016 1.0000 0.2642
-5.250 -0.5930 0.02230 0.01163 -0.0001 1.0000 0.2955
-5.000 -0.5740 0.02160 0.01099 0.0014 1.0000 0.3306
-4.750 -0.5552 0.02094 0.01046 0.0031 1.0000 0.3674
-4.500 -0.5362 0.02035 0.00994 0.0047 1.0000 0.4072
-4.250 -0.5170 0.01981 0.00953 0.0065 1.0000 0.4489
-4.000 -0.4983 0.01934 0.00919 0.0084 1.0000 0.4916
-3.750 -0.4797 0.01893 0.00891 0.0105 1.0000 0.5350
-3.500 -0.4606 0.01858 0.00868 0.0126 1.0000 0.5786
-3.250 -0.4412 0.01829 0.00848 0.0148 1.0000 0.6220
-3.000 -0.4210 0.01806 0.00835 0.0169 1.0000 0.6651
-2.750 -0.3996 0.01790 0.00827 0.0189 1.0000 0.7072
-2.500 -0.3760 0.01781 0.00824 0.0205 1.0000 0.7482
-2.250 -0.3492 0.01779 0.00822 0.0216 1.0000 0.7883
-2.000 -0.3183 0.01783 0.00825 0.0217 1.0000 0.8269
-1.750 -0.2789 0.01797 0.00833 0.0202 1.0000 0.8614
-1.500 -0.2350 0.01813 0.00838 0.0175 1.0000 0.8927
-1.250 -0.1866 0.01827 0.00841 0.0137 1.0000 0.9198
-1.000 -0.1359 0.01834 0.00838 0.0091 1.0000 0.9441
-0.750 -0.0852 0.01833 0.00830 0.0042 1.0000 0.9671
-0.500 -0.0324 0.01822 0.00813 -0.0014 1.0000 0.9881
-0.250 0.0008 0.01808 0.00798 -0.0038 1.0000 1.0000
0.000 0.0000 0.01803 0.00794 0.0000 1.0000 1.0000
0.250 -0.0008 0.01808 0.00798 0.0038 1.0000 1.0000
0.500 0.0325 0.01822 0.00813 0.0014 0.9880 1.0000
0.750 0.0852 0.01833 0.00829 -0.0042 0.9671 1.0000
1.000 0.1360 0.01834 0.00838 -0.0091 0.9441 1.0000
1.250 0.1865 0.01827 0.00841 -0.0137 0.9198 1.0000
1.500 0.2350 0.01813 0.00837 -0.0175 0.8927 1.0000
1.750 0.2789 0.01797 0.00833 -0.0202 0.8615 1.0000
2.000 0.3183 0.01783 0.00824 -0.0217 0.8269 1.0000
2.250 0.3492 0.01779 0.00822 -0.0215 0.7884 1.0000
2.500 0.3760 0.01781 0.00824 -0.0205 0.7484 1.0000
2.750 0.3996 0.01790 0.00827 -0.0189 0.7073 1.0000
3.000 0.4210 0.01806 0.00835 -0.0169 0.6653 1.0000
3.250 0.4412 0.01829 0.00848 -0.0148 0.6221 1.0000
3.500 0.4606 0.01858 0.00868 -0.0127 0.5788 1.0000
3.750 0.4797 0.01893 0.00891 -0.0105 0.5351 1.0000
4.000 0.4983 0.01934 0.00918 -0.0084 0.4917 1.0000
4.250 0.5170 0.01981 0.00953 -0.0065 0.4489 1.0000
4.500 0.5361 0.02035 0.00994 -0.0047 0.4071 1.0000
4.750 0.5552 0.02094 0.01046 -0.0031 0.3675 1.0000
5.000 0.5739 0.02160 0.01098 -0.0014 0.3307 1.0000
5.250 0.5931 0.02230 0.01163 0.0001 0.2957 1.0000
5.500 0.6121 0.02307 0.01233 0.0016 0.2642 1.0000
5.750 0.6309 0.02390 0.01309 0.0031 0.2354 1.0000
6.250 0.6681 0.02576 0.01486 0.0060 0.1876 1.0000
6.500 0.6872 0.02679 0.01598 0.0074 0.1665 1.0000
6.750 0.7052 0.02787 0.01704 0.0089 0.1481 1.0000
7.000 0.7232 0.02905 0.01821 0.0103 0.1322 1.0000
7.250 0.7408 0.03030 0.01949 0.0118 0.1173 1.0000
7.500 0.7580 0.03162 0.02091 0.0132 0.1046 1.0000
7.750 0.7755 0.03311 0.02260 0.0147 0.0933 1.0000
8.000 0.7923 0.03481 0.02452 0.0162 0.0838 1.0000
8.250 0.8082 0.03647 0.02616 0.0175 0.0769 1.0000
8.500 0.8241 0.03885 0.02897 0.0191 0.0714 1.0000
8.750 0.8384 0.04064 0.03082 0.0205 0.0666 1.0000
9.000 0.8483 0.04320 0.03376 0.0222 0.0621 1.0000
9.250 0.8558 0.04597 0.03692 0.0240 0.0588 1.0000
9.500 0.8617 0.04883 0.04011 0.0257 0.0566 1.0000
9.750 0.8661 0.05165 0.04314 0.0273 0.0550 1.0000
10.000 0.8699 0.05453 0.04612 0.0287 0.0535 1.0000
10.250 0.8591 0.05834 0.05027 0.0305 0.0528 1.0000
10.500 0.8401 0.06217 0.05439 0.0324 0.0523 1.0000
10.750 0.8186 0.06634 0.05876 0.0331 0.0523 1.0000
11.000 0.7957 0.07140 0.06398 0.0316 0.0524 1.0000
11.250 0.7742 0.07736 0.07004 0.0283 0.0528 1.0000
11.500 0.7518 0.08462 0.07735 0.0236 0.0531 1.0000
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Polar data table (+)
Polar graphs
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