SD8020-010-88 (sd8020-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD8020-010-88 (sd8020-il) Reynolds number: 100,000 Max Cl/Cd: 36.9 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd8020-il-100000.txt Download as CSV file: xf-sd8020-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.7179 0.09382 0.08875 -0.0202 1.0000 0.0673
-11.250 -0.7252 0.08734 0.08230 -0.0227 1.0000 0.0667
-11.000 -0.7390 0.08039 0.07535 -0.0263 1.0000 0.0657
-10.750 -0.7570 0.07366 0.06861 -0.0301 1.0000 0.0637
-10.500 -0.7886 0.06691 0.06176 -0.0335 1.0000 0.0619
-10.250 -0.8757 0.05903 0.05314 -0.0309 1.0000 0.0558
-10.000 -0.8861 0.05554 0.04931 -0.0286 1.0000 0.0555
-9.750 -0.8935 0.05100 0.04445 -0.0264 1.0000 0.0558
-9.500 -0.8852 0.04772 0.04119 -0.0254 1.0000 0.0581
-9.250 -0.8759 0.04548 0.03884 -0.0238 1.0000 0.0607
-9.000 -0.8737 0.04204 0.03499 -0.0213 1.0000 0.0619
-8.750 -0.8679 0.03869 0.03116 -0.0188 1.0000 0.0632
-8.500 -0.8584 0.03576 0.02772 -0.0163 1.0000 0.0652
-8.250 -0.8464 0.03308 0.02460 -0.0141 1.0000 0.0687
-8.000 -0.8284 0.03124 0.02272 -0.0129 1.0000 0.0736
-7.750 -0.8104 0.02920 0.02030 -0.0110 1.0000 0.0786
-7.500 -0.7913 0.02731 0.01841 -0.0097 1.0000 0.0860
-7.250 -0.7721 0.02560 0.01653 -0.0081 1.0000 0.0956
-7.000 -0.7528 0.02416 0.01499 -0.0064 1.0000 0.1079
-6.750 -0.7342 0.02290 0.01381 -0.0049 1.0000 0.1234
-6.500 -0.7157 0.02185 0.01280 -0.0033 1.0000 0.1413
-6.250 -0.6972 0.02097 0.01183 -0.0016 1.0000 0.1624
-6.000 -0.6785 0.01998 0.01103 -0.0001 1.0000 0.1836
-5.750 -0.6596 0.01910 0.01022 0.0015 1.0000 0.2084
-5.500 -0.6407 0.01827 0.00949 0.0032 1.0000 0.2360
-5.250 -0.6221 0.01747 0.00884 0.0049 1.0000 0.2670
-5.000 -0.6038 0.01673 0.00827 0.0066 1.0000 0.3025
-4.750 -0.5856 0.01605 0.00779 0.0085 1.0000 0.3419
-4.500 -0.5674 0.01544 0.00738 0.0103 1.0000 0.3850
-4.250 -0.5494 0.01489 0.00704 0.0123 1.0000 0.4305
-4.000 -0.5313 0.01440 0.00675 0.0144 1.0000 0.4783
-3.750 -0.5131 0.01399 0.00652 0.0165 1.0000 0.5278
-3.500 -0.4949 0.01363 0.00639 0.0187 1.0000 0.5760
-3.250 -0.4766 0.01335 0.00630 0.0210 1.0000 0.6245
-3.000 -0.4582 0.01313 0.00623 0.0234 1.0000 0.6727
-2.750 -0.4396 0.01298 0.00622 0.0259 1.0000 0.7196
-2.500 -0.4204 0.01291 0.00627 0.0284 1.0000 0.7650
-2.250 -0.3993 0.01292 0.00638 0.0306 1.0000 0.8092
-2.000 -0.3722 0.01306 0.00656 0.0317 1.0000 0.8515
-1.750 -0.3325 0.01340 0.00688 0.0305 1.0000 0.8895
-1.500 -0.2789 0.01385 0.00723 0.0264 1.0000 0.9200
-1.250 -0.2166 0.01427 0.00754 0.0203 1.0000 0.9436
-1.000 -0.1453 0.01453 0.00767 0.0120 1.0000 0.9609
-0.750 -0.0773 0.01457 0.00763 0.0040 1.0000 0.9784
-0.500 -0.0075 0.01442 0.00742 -0.0047 1.0000 0.9942
-0.250 0.0172 0.01417 0.00718 -0.0059 1.0000 1.0000
0.000 -0.0001 0.01411 0.00713 0.0000 1.0000 1.0000
0.250 -0.0172 0.01417 0.00718 0.0060 1.0000 1.0000
0.500 0.0075 0.01442 0.00742 0.0047 0.9942 1.0000
0.750 0.0770 0.01457 0.00763 -0.0039 0.9784 1.0000
1.000 0.1454 0.01453 0.00767 -0.0120 0.9609 1.0000
1.250 0.2167 0.01427 0.00754 -0.0203 0.9436 1.0000
1.500 0.2789 0.01385 0.00723 -0.0264 0.9200 1.0000
1.750 0.3324 0.01340 0.00688 -0.0305 0.8896 1.0000
2.000 0.3723 0.01306 0.00656 -0.0317 0.8516 1.0000
2.250 0.3992 0.01292 0.00638 -0.0306 0.8094 1.0000
2.500 0.4204 0.01291 0.00627 -0.0283 0.7651 1.0000
2.750 0.4396 0.01298 0.00622 -0.0259 0.7198 1.0000
3.000 0.4582 0.01313 0.00623 -0.0234 0.6728 1.0000
3.250 0.4766 0.01335 0.00630 -0.0210 0.6247 1.0000
3.500 0.4949 0.01363 0.00639 -0.0187 0.5761 1.0000
3.750 0.5131 0.01399 0.00652 -0.0165 0.5278 1.0000
4.000 0.5313 0.01441 0.00675 -0.0143 0.4784 1.0000
4.250 0.5494 0.01489 0.00704 -0.0123 0.4307 1.0000
4.500 0.5674 0.01544 0.00738 -0.0103 0.3849 1.0000
4.750 0.5855 0.01605 0.00779 -0.0084 0.3417 1.0000
5.000 0.6037 0.01673 0.00827 -0.0066 0.3025 1.0000
5.250 0.6221 0.01746 0.00884 -0.0049 0.2670 1.0000
5.500 0.6407 0.01827 0.00948 -0.0032 0.2359 1.0000
5.750 0.6595 0.01910 0.01021 -0.0015 0.2082 1.0000
6.000 0.6784 0.01997 0.01103 0.0001 0.1833 1.0000
6.250 0.6971 0.02097 0.01183 0.0016 0.1621 1.0000
6.500 0.7157 0.02186 0.01281 0.0033 0.1411 1.0000
6.750 0.7342 0.02292 0.01383 0.0049 0.1233 1.0000
7.000 0.7529 0.02418 0.01501 0.0064 0.1079 1.0000
7.250 0.7722 0.02561 0.01653 0.0080 0.0956 1.0000
7.500 0.7913 0.02731 0.01842 0.0097 0.0860 1.0000
7.750 0.8106 0.02922 0.02030 0.0109 0.0788 1.0000
8.000 0.8284 0.03127 0.02275 0.0129 0.0738 1.0000
8.250 0.8464 0.03309 0.02466 0.0142 0.0691 1.0000
8.500 0.8586 0.03578 0.02773 0.0163 0.0653 1.0000
8.750 0.8680 0.03870 0.03118 0.0188 0.0633 1.0000
9.000 0.8737 0.04206 0.03501 0.0213 0.0620 1.0000
9.250 0.8757 0.04553 0.03891 0.0238 0.0609 1.0000
9.500 0.8851 0.04771 0.04120 0.0254 0.0582 1.0000
9.750 0.8934 0.05111 0.04456 0.0264 0.0558 1.0000
10.000 0.8865 0.05546 0.04923 0.0286 0.0556 1.0000
10.250 0.8758 0.05903 0.05315 0.0309 0.0558 1.0000
10.500 0.7900 0.06673 0.06157 0.0335 0.0615 1.0000
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Polar data table (+)
Polar graphs
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