S9026 (9.5%) (s9026-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9026 (9.5%) (s9026-il) Reynolds number: 50,000 Max Cl/Cd: 25.37 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9026-il-50000-n5.txt Download as CSV file: xf-s9026-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S9026 (9.5%)
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.7264 0.09430 0.08699 -0.0035 1.0000 0.0646
-10.750 -0.7523 0.08363 0.07639 -0.0109 1.0000 0.0639
-10.500 -0.7865 0.07377 0.06649 -0.0186 1.0000 0.0628
-10.250 -0.8185 0.06693 0.05953 -0.0223 1.0000 0.0622
-10.000 -0.8427 0.06199 0.05440 -0.0226 1.0000 0.0620
-9.750 -0.8570 0.05740 0.04952 -0.0223 1.0000 0.0625
-9.500 -0.8640 0.05316 0.04491 -0.0216 1.0000 0.0636
-9.250 -0.8654 0.04925 0.04054 -0.0206 1.0000 0.0656
-9.000 -0.8636 0.04547 0.03611 -0.0193 1.0000 0.0683
-8.750 -0.8478 0.04359 0.03429 -0.0186 1.0000 0.0719
-8.500 -0.8339 0.04111 0.03153 -0.0176 1.0000 0.0754
-8.250 -0.8189 0.03831 0.02819 -0.0164 1.0000 0.0794
-8.000 -0.8013 0.03644 0.02622 -0.0155 1.0000 0.0848
-7.750 -0.7828 0.03466 0.02416 -0.0146 1.0000 0.0919
-7.500 -0.7628 0.03287 0.02226 -0.0136 1.0000 0.0984
-7.250 -0.7426 0.03133 0.02044 -0.0127 1.0000 0.1083
-7.000 -0.7222 0.03002 0.01914 -0.0118 1.0000 0.1179
-6.750 -0.7014 0.02873 0.01776 -0.0108 1.0000 0.1296
-6.500 -0.6802 0.02753 0.01650 -0.0099 1.0000 0.1431
-6.250 -0.6586 0.02637 0.01529 -0.0089 1.0000 0.1580
-6.000 -0.6370 0.02533 0.01419 -0.0080 1.0000 0.1769
-5.750 -0.6154 0.02432 0.01323 -0.0070 1.0000 0.1958
-5.500 -0.5939 0.02342 0.01231 -0.0061 1.0000 0.2202
-5.250 -0.5726 0.02257 0.01155 -0.0051 1.0000 0.2469
-5.000 -0.5511 0.02179 0.01084 -0.0041 1.0000 0.2778
-4.750 -0.5298 0.02106 0.01025 -0.0030 1.0000 0.3118
-4.500 -0.5084 0.02039 0.00966 -0.0019 1.0000 0.3488
-4.250 -0.4872 0.01977 0.00919 -0.0006 1.0000 0.3879
-4.000 -0.4665 0.01922 0.00877 0.0008 1.0000 0.4292
-3.750 -0.4462 0.01872 0.00843 0.0024 1.0000 0.4720
-3.500 -0.4261 0.01828 0.00813 0.0042 1.0000 0.5161
-3.250 -0.4061 0.01790 0.00790 0.0061 1.0000 0.5610
-3.000 -0.3860 0.01758 0.00773 0.0082 1.0000 0.6058
-2.750 -0.3658 0.01731 0.00760 0.0103 1.0000 0.6500
-2.500 -0.3453 0.01710 0.00748 0.0124 1.0000 0.6935
-2.250 -0.3240 0.01693 0.00741 0.0145 1.0000 0.7366
-2.000 -0.3012 0.01682 0.00737 0.0163 1.0000 0.7793
-1.750 -0.2743 0.01677 0.00736 0.0173 1.0000 0.8205
-1.500 -0.2403 0.01677 0.00735 0.0169 1.0000 0.8597
-1.250 -0.2003 0.01680 0.00734 0.0150 1.0000 0.8967
-1.000 -0.1510 0.01685 0.00730 0.0111 1.0000 0.9285
-0.750 -0.0972 0.01685 0.00723 0.0060 1.0000 0.9567
-0.500 -0.0422 0.01676 0.00709 0.0003 1.0000 0.9827
-0.250 -0.0008 0.01660 0.00690 -0.0035 1.0000 1.0000
0.000 0.0000 0.01655 0.00687 0.0000 1.0000 1.0000
0.250 0.0008 0.01660 0.00691 0.0035 1.0000 1.0000
0.500 0.0423 0.01676 0.00709 -0.0003 0.9826 1.0000
0.750 0.0973 0.01685 0.00723 -0.0060 0.9567 1.0000
1.000 0.1510 0.01685 0.00730 -0.0111 0.9285 1.0000
1.250 0.2003 0.01680 0.00734 -0.0150 0.8967 1.0000
1.500 0.2403 0.01677 0.00735 -0.0169 0.8597 1.0000
1.750 0.2744 0.01677 0.00736 -0.0173 0.8206 1.0000
2.000 0.3013 0.01682 0.00737 -0.0163 0.7792 1.0000
2.250 0.3241 0.01693 0.00741 -0.0145 0.7365 1.0000
2.500 0.3453 0.01710 0.00748 -0.0124 0.6934 1.0000
2.750 0.3659 0.01731 0.00760 -0.0103 0.6499 1.0000
3.000 0.3861 0.01758 0.00773 -0.0082 0.6058 1.0000
3.250 0.4062 0.01790 0.00791 -0.0062 0.5610 1.0000
3.500 0.4262 0.01828 0.00813 -0.0042 0.5162 1.0000
3.750 0.4463 0.01872 0.00843 -0.0025 0.4721 1.0000
4.000 0.4665 0.01922 0.00877 -0.0008 0.4291 1.0000
4.250 0.4873 0.01977 0.00919 0.0006 0.3878 1.0000
4.500 0.5085 0.02039 0.00966 0.0018 0.3487 1.0000
4.750 0.5299 0.02106 0.01025 0.0030 0.3117 1.0000
5.000 0.5511 0.02179 0.01084 0.0040 0.2778 1.0000
5.250 0.5726 0.02257 0.01155 0.0051 0.2469 1.0000
5.500 0.5939 0.02342 0.01231 0.0061 0.2203 1.0000
5.750 0.6155 0.02432 0.01323 0.0070 0.1958 1.0000
6.000 0.6370 0.02533 0.01419 0.0080 0.1769 1.0000
6.250 0.6585 0.02637 0.01529 0.0089 0.1580 1.0000
6.500 0.6801 0.02753 0.01650 0.0099 0.1431 1.0000
6.750 0.7013 0.02873 0.01776 0.0108 0.1295 1.0000
7.000 0.7221 0.03002 0.01913 0.0118 0.1180 1.0000
7.250 0.7426 0.03134 0.02043 0.0127 0.1082 1.0000
7.500 0.7627 0.03287 0.02226 0.0137 0.0983 1.0000
7.750 0.7827 0.03465 0.02415 0.0146 0.0919 1.0000
8.000 0.8012 0.03643 0.02621 0.0156 0.0847 1.0000
8.250 0.8188 0.03831 0.02819 0.0165 0.0794 1.0000
8.500 0.8338 0.04111 0.03152 0.0176 0.0754 1.0000
8.750 0.8477 0.04357 0.03427 0.0186 0.0718 1.0000
9.000 0.8634 0.04545 0.03610 0.0194 0.0684 1.0000
9.250 0.8653 0.04923 0.04051 0.0206 0.0656 1.0000
9.500 0.8638 0.05315 0.04490 0.0216 0.0636 1.0000
9.750 0.8570 0.05739 0.04950 0.0223 0.0625 1.0000
10.000 0.8428 0.06197 0.05438 0.0226 0.0621 1.0000
10.250 0.8184 0.06693 0.05953 0.0223 0.0621 1.0000
10.500 0.7868 0.07376 0.06648 0.0186 0.0628 1.0000
10.750 0.7526 0.08364 0.07640 0.0109 0.0639 1.0000
11.000 0.7266 0.09434 0.08702 0.0034 0.0645 1.0000
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Polar data table (+)
Polar graphs
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