S9032 (9%) (s9032-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9032 (9%) (s9032-il) Reynolds number: 50,000 Max Cl/Cd: 25.02 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9032-il-50000-n5.txt Download as CSV file: xf-s9032-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S9032 (9%)
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.7607 0.08641 0.07916 -0.0075 1.0000 0.0621
-10.500 -0.7829 0.07824 0.07097 -0.0136 1.0000 0.0618
-10.250 -0.8069 0.07158 0.06426 -0.0180 1.0000 0.0614
-10.000 -0.8306 0.06635 0.05894 -0.0194 1.0000 0.0612
-9.750 -0.8491 0.06130 0.05363 -0.0200 1.0000 0.0614
-9.500 -0.8613 0.05639 0.04832 -0.0199 1.0000 0.0618
-9.250 -0.8660 0.05180 0.04326 -0.0193 1.0000 0.0626
-9.000 -0.8562 0.04876 0.04004 -0.0186 1.0000 0.0641
-8.750 -0.8451 0.04596 0.03701 -0.0178 1.0000 0.0661
-8.500 -0.8331 0.04333 0.03408 -0.0169 1.0000 0.0696
-8.250 -0.8211 0.04034 0.03051 -0.0160 1.0000 0.0741
-8.000 -0.8039 0.03818 0.02823 -0.0151 1.0000 0.0782
-7.750 -0.7852 0.03605 0.02587 -0.0143 1.0000 0.0828
-7.500 -0.7660 0.03391 0.02335 -0.0133 1.0000 0.0895
-7.250 -0.7460 0.03248 0.02182 -0.0125 1.0000 0.0975
-7.000 -0.7247 0.03076 0.01993 -0.0116 1.0000 0.1054
-6.750 -0.7034 0.02937 0.01836 -0.0108 1.0000 0.1167
-6.500 -0.6816 0.02809 0.01695 -0.0099 1.0000 0.1288
-6.250 -0.6597 0.02692 0.01572 -0.0091 1.0000 0.1429
-6.000 -0.6377 0.02579 0.01461 -0.0082 1.0000 0.1583
-5.750 -0.6154 0.02469 0.01350 -0.0073 1.0000 0.1748
-5.500 -0.5932 0.02374 0.01256 -0.0065 1.0000 0.1970
-5.250 -0.5709 0.02282 0.01170 -0.0056 1.0000 0.2204
-5.000 -0.5485 0.02198 0.01093 -0.0047 1.0000 0.2488
-4.750 -0.5260 0.02121 0.01025 -0.0039 1.0000 0.2817
-4.500 -0.5035 0.02050 0.00961 -0.0030 1.0000 0.3173
-4.250 -0.4811 0.01985 0.00907 -0.0020 1.0000 0.3568
-4.000 -0.4592 0.01925 0.00862 -0.0008 1.0000 0.3970
-3.750 -0.4378 0.01871 0.00823 0.0005 1.0000 0.4396
-3.500 -0.4165 0.01822 0.00787 0.0021 1.0000 0.4843
-3.250 -0.3955 0.01779 0.00760 0.0037 1.0000 0.5309
-3.000 -0.3747 0.01741 0.00738 0.0056 1.0000 0.5775
-2.750 -0.3538 0.01707 0.00720 0.0075 1.0000 0.6236
-2.500 -0.3328 0.01677 0.00702 0.0095 1.0000 0.6694
-2.250 -0.3112 0.01651 0.00689 0.0116 1.0000 0.7153
-2.000 -0.2882 0.01631 0.00680 0.0134 1.0000 0.7619
-1.750 -0.2615 0.01617 0.00674 0.0145 1.0000 0.8094
-1.500 -0.2261 0.01611 0.00669 0.0140 1.0000 0.8558
-1.250 -0.1817 0.01609 0.00664 0.0114 1.0000 0.8990
-1.000 -0.1305 0.01607 0.00653 0.0071 1.0000 0.9366
-0.750 -0.0750 0.01601 0.00639 0.0016 1.0000 0.9700
-0.500 -0.0167 0.01584 0.00615 -0.0050 1.0000 1.0000
-0.250 -0.0087 0.01571 0.00602 -0.0025 1.0000 1.0000
0.000 0.0000 0.01566 0.00598 0.0000 1.0000 1.0000
0.250 0.0087 0.01571 0.00602 0.0025 1.0000 1.0000
0.500 0.0167 0.01584 0.00615 0.0050 1.0000 1.0000
0.750 0.0750 0.01601 0.00639 -0.0016 0.9700 1.0000
1.000 0.1305 0.01607 0.00653 -0.0071 0.9365 1.0000
1.250 0.1817 0.01609 0.00664 -0.0114 0.8989 1.0000
1.500 0.2262 0.01611 0.00669 -0.0140 0.8558 1.0000
1.750 0.2616 0.01617 0.00674 -0.0146 0.8095 1.0000
2.000 0.2884 0.01631 0.00680 -0.0134 0.7618 1.0000
2.250 0.3114 0.01651 0.00689 -0.0116 0.7152 1.0000
2.500 0.3330 0.01677 0.00702 -0.0096 0.6693 1.0000
2.750 0.3540 0.01707 0.00720 -0.0076 0.6235 1.0000
3.000 0.3749 0.01741 0.00738 -0.0056 0.5774 1.0000
3.250 0.3957 0.01779 0.00760 -0.0038 0.5308 1.0000
3.500 0.4167 0.01822 0.00787 -0.0021 0.4842 1.0000
3.750 0.4380 0.01871 0.00823 -0.0006 0.4394 1.0000
4.000 0.4594 0.01925 0.00862 0.0008 0.3969 1.0000
4.250 0.4812 0.01985 0.00907 0.0020 0.3566 1.0000
4.500 0.5036 0.02050 0.00961 0.0030 0.3174 1.0000
4.750 0.5261 0.02122 0.01025 0.0039 0.2816 1.0000
5.000 0.5486 0.02198 0.01093 0.0047 0.2488 1.0000
5.250 0.5709 0.02282 0.01171 0.0056 0.2204 1.0000
5.500 0.5932 0.02374 0.01256 0.0065 0.1970 1.0000
5.750 0.6154 0.02469 0.01350 0.0073 0.1748 1.0000
6.000 0.6376 0.02578 0.01461 0.0082 0.1584 1.0000
6.250 0.6596 0.02691 0.01572 0.0091 0.1429 1.0000
6.500 0.6814 0.02809 0.01694 0.0099 0.1288 1.0000
6.750 0.7032 0.02937 0.01835 0.0108 0.1167 1.0000
7.000 0.7245 0.03075 0.01993 0.0117 0.1054 1.0000
7.250 0.7457 0.03247 0.02180 0.0126 0.0976 1.0000
7.500 0.7657 0.03391 0.02335 0.0134 0.0896 1.0000
7.750 0.7848 0.03603 0.02585 0.0143 0.0828 1.0000
8.000 0.8035 0.03816 0.02821 0.0152 0.0782 1.0000
8.250 0.8207 0.04032 0.03048 0.0160 0.0742 1.0000
8.500 0.8326 0.04329 0.03404 0.0170 0.0696 1.0000
8.750 0.8446 0.04592 0.03697 0.0179 0.0661 1.0000
9.000 0.8555 0.04874 0.04001 0.0187 0.0642 1.0000
9.250 0.8654 0.05176 0.04321 0.0194 0.0626 1.0000
9.500 0.8609 0.05631 0.04823 0.0200 0.0618 1.0000
9.750 0.8489 0.06120 0.05352 0.0201 0.0614 1.0000
10.000 0.8307 0.06623 0.05881 0.0196 0.0613 1.0000
10.250 0.8073 0.07141 0.06408 0.0182 0.0614 1.0000
10.500 0.7831 0.07807 0.07080 0.0139 0.0618 1.0000
10.750 0.7604 0.08634 0.07909 0.0076 0.0621 1.0000
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Polar data table (+)
Polar graphs
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