S9026 (9.5%) (s9026-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9026 (9.5%) (s9026-il) Reynolds number: 50,000 Max Cl/Cd: 24.18 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9026-il-50000.txt Download as CSV file: xf-s9026-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6904 0.08866 0.08156 -0.0017 1.0000 0.1767
-9.000 -0.7300 0.07828 0.07130 -0.0097 1.0000 0.1620
-8.750 -0.7836 0.06768 0.06044 -0.0155 1.0000 0.1491
-8.500 -0.7877 0.06222 0.05478 -0.0160 1.0000 0.1484
-8.250 -0.7910 0.05681 0.04906 -0.0160 1.0000 0.1478
-8.000 -0.7917 0.05158 0.04338 -0.0156 1.0000 0.1479
-7.750 -0.7901 0.04677 0.03788 -0.0147 1.0000 0.1494
-7.500 -0.7696 0.04452 0.03577 -0.0138 1.0000 0.1589
-7.250 -0.7605 0.04067 0.03129 -0.0126 1.0000 0.1651
-7.000 -0.7410 0.03809 0.02856 -0.0115 1.0000 0.1741
-6.750 -0.7228 0.03585 0.02614 -0.0103 1.0000 0.1874
-6.500 -0.7032 0.03350 0.02356 -0.0091 1.0000 0.2006
-6.250 -0.6835 0.03159 0.02143 -0.0079 1.0000 0.2185
-6.000 -0.6624 0.02964 0.01931 -0.0067 1.0000 0.2369
-5.750 -0.6406 0.02817 0.01791 -0.0054 1.0000 0.2602
-5.500 -0.6187 0.02666 0.01641 -0.0041 1.0000 0.2860
-5.250 -0.5973 0.02534 0.01516 -0.0027 1.0000 0.3169
-5.000 -0.5764 0.02413 0.01402 -0.0011 1.0000 0.3532
-4.750 -0.5559 0.02310 0.01318 0.0008 1.0000 0.3942
-4.500 -0.5359 0.02217 0.01244 0.0028 1.0000 0.4400
-4.250 -0.5159 0.02136 0.01190 0.0052 1.0000 0.4877
-4.000 -0.4967 0.02069 0.01145 0.0079 1.0000 0.5393
-3.750 -0.4777 0.02016 0.01116 0.0109 1.0000 0.5917
-3.500 -0.4596 0.01974 0.01092 0.0142 1.0000 0.6458
-3.250 -0.4410 0.01953 0.01087 0.0181 1.0000 0.6968
-3.000 -0.4235 0.01937 0.01080 0.0221 1.0000 0.7491
-2.750 -0.3997 0.01943 0.01091 0.0257 1.0000 0.7990
-2.500 -0.3642 0.01961 0.01100 0.0270 1.0000 0.8514
-2.250 -0.2781 0.02024 0.01128 0.0192 1.0000 0.9025
-2.000 -0.1612 0.02019 0.01078 0.0035 1.0000 0.9501
-1.750 -0.0572 0.01914 0.00940 -0.0121 1.0000 0.9920
-1.500 -0.0283 0.01830 0.00850 -0.0149 1.0000 1.0000
-1.250 -0.0199 0.01776 0.00797 -0.0136 1.0000 1.0000
-1.000 -0.0125 0.01733 0.00755 -0.0118 1.0000 1.0000
-0.750 -0.0066 0.01700 0.00724 -0.0095 1.0000 1.0000
-0.500 -0.0028 0.01675 0.00703 -0.0067 1.0000 1.0000
-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 0.0028 0.01675 0.00703 0.0067 1.0000 1.0000
0.750 0.0066 0.01700 0.00724 0.0095 1.0000 1.0000
1.000 0.0125 0.01733 0.00755 0.0118 1.0000 1.0000
1.250 0.0199 0.01776 0.00797 0.0136 1.0000 1.0000
1.500 0.0282 0.01830 0.00850 0.0149 1.0000 1.0000
1.750 0.0573 0.01913 0.00940 0.0121 0.9920 1.0000
2.000 0.1614 0.02019 0.01077 -0.0035 0.9499 1.0000
2.250 0.2784 0.02023 0.01128 -0.0193 0.9024 1.0000
2.500 0.3642 0.01961 0.01100 -0.0270 0.8513 1.0000
2.750 0.3998 0.01942 0.01091 -0.0257 0.7988 1.0000
3.000 0.4236 0.01937 0.01080 -0.0222 0.7491 1.0000
3.250 0.4411 0.01953 0.01087 -0.0181 0.6967 1.0000
3.500 0.4598 0.01974 0.01092 -0.0143 0.6458 1.0000
3.750 0.4778 0.02016 0.01116 -0.0109 0.5916 1.0000
4.000 0.4968 0.02069 0.01146 -0.0079 0.5393 1.0000
4.250 0.5160 0.02136 0.01190 -0.0052 0.4876 1.0000
4.500 0.5360 0.02217 0.01244 -0.0028 0.4399 1.0000
4.750 0.5559 0.02310 0.01318 -0.0008 0.3941 1.0000
5.000 0.5765 0.02413 0.01402 0.0011 0.3532 1.0000
5.250 0.5974 0.02534 0.01517 0.0026 0.3168 1.0000
5.500 0.6188 0.02666 0.01641 0.0041 0.2860 1.0000
5.750 0.6406 0.02816 0.01791 0.0054 0.2602 1.0000
6.000 0.6624 0.02964 0.01931 0.0067 0.2369 1.0000
6.250 0.6835 0.03159 0.02143 0.0079 0.2185 1.0000
6.500 0.7032 0.03350 0.02356 0.0091 0.2005 1.0000
6.750 0.7227 0.03585 0.02613 0.0103 0.1873 1.0000
7.000 0.7410 0.03809 0.02856 0.0115 0.1741 1.0000
7.250 0.7606 0.04066 0.03127 0.0126 0.1650 1.0000
7.500 0.7695 0.04451 0.03577 0.0138 0.1587 1.0000
7.750 0.7899 0.04676 0.03787 0.0147 0.1494 1.0000
8.000 0.7915 0.05159 0.04339 0.0157 0.1479 1.0000
8.250 0.7908 0.05681 0.04906 0.0160 0.1478 1.0000
8.500 0.7876 0.06222 0.05477 0.0160 0.1484 1.0000
8.750 0.7829 0.06771 0.06046 0.0155 0.1491 1.0000
9.000 0.7305 0.07822 0.07124 0.0097 0.1620 1.0000
9.250 0.6856 0.08945 0.08235 0.0004 0.1798 1.0000
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Polar data table (+)
Polar graphs
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