NASA/LANGLEY RC-10(B)3 AIRFOIL (rc10b3-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-10(B)3 AIRFOIL (rc10b3-il) Reynolds number: 50,000 Max Cl/Cd: 33.77 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rc10b3-il-50000.txt Download as CSV file: xf-rc10b3-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC-10(B)3 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5043 0.10836 0.10138 -0.0060 1.0000 0.2519
-8.750 -0.5103 0.10594 0.09903 -0.0067 1.0000 0.2650
-8.500 -0.5034 0.10234 0.09546 -0.0059 1.0000 0.2803
-8.250 -0.5037 0.09925 0.09244 -0.0055 1.0000 0.2963
-8.000 -0.4831 0.09493 0.08812 -0.0033 1.0000 0.3167
-7.750 -0.4753 0.09186 0.08509 -0.0018 1.0000 0.3391
-7.500 -0.4963 0.09005 0.08344 -0.0012 1.0000 0.3594
-7.250 -0.4705 0.08613 0.07950 0.0016 1.0000 0.3886
-7.000 -0.4600 0.08311 0.07650 0.0042 1.0000 0.4195
-6.750 -0.4711 0.08138 0.07489 0.0077 1.0000 0.4538
-6.500 -0.4483 0.07836 0.07187 0.0117 1.0000 0.5007
-6.250 -0.3990 0.07426 0.06769 0.0151 1.0000 0.5666
-5.250 -0.4214 0.06250 0.05635 0.0200 1.0000 0.5819
-5.000 -0.5393 0.05030 0.04200 -0.0065 1.0000 0.1720
-4.750 -0.5234 0.04605 0.03749 -0.0049 1.0000 0.1532
-4.500 -0.5096 0.04290 0.03368 -0.0024 1.0000 0.1392
-4.250 -0.4941 0.04009 0.03064 -0.0005 1.0000 0.1355
-4.000 -0.4776 0.03771 0.02784 0.0015 1.0000 0.1340
-3.750 -0.4591 0.03555 0.02527 0.0033 1.0000 0.1338
-3.500 -0.4381 0.03348 0.02281 0.0049 1.0000 0.1333
-3.250 -0.4149 0.03158 0.02054 0.0062 1.0000 0.1338
-3.000 -0.3909 0.03002 0.01861 0.0074 1.0000 0.1379
-2.750 -0.1090 0.02055 0.01231 -0.0319 1.0000 1.0000
-2.500 -0.0998 0.02060 0.01187 -0.0288 1.0000 1.0000
-2.250 -0.0917 0.02066 0.01162 -0.0257 1.0000 1.0000
-2.000 -0.0835 0.02076 0.01144 -0.0227 1.0000 1.0000
-1.750 -0.0750 0.02087 0.01131 -0.0198 1.0000 1.0000
-1.500 -0.0661 0.02101 0.01125 -0.0170 1.0000 1.0000
-1.250 -0.0569 0.02118 0.01122 -0.0142 1.0000 1.0000
-1.000 -0.0471 0.02137 0.01124 -0.0116 1.0000 1.0000
-0.750 -0.0370 0.02159 0.01130 -0.0091 1.0000 1.0000
-0.500 -0.0265 0.02183 0.01139 -0.0068 1.0000 1.0000
-0.250 -0.0156 0.02211 0.01153 -0.0045 1.0000 1.0000
0.000 -0.0043 0.02241 0.01171 -0.0024 1.0000 1.0000
0.250 0.0073 0.02274 0.01194 -0.0003 1.0000 1.0000
0.500 0.0191 0.02311 0.01222 0.0016 1.0000 1.0000
0.750 0.0311 0.02352 0.01253 0.0034 1.0000 1.0000
1.000 0.0433 0.02396 0.01290 0.0051 1.0000 1.0000
1.250 0.0555 0.02445 0.01333 0.0067 1.0000 1.0000
1.500 0.0679 0.02499 0.01382 0.0082 1.0000 1.0000
1.750 0.0804 0.02558 0.01437 0.0095 1.0000 1.0000
2.000 0.0930 0.02622 0.01499 0.0107 1.0000 1.0000
2.250 0.1158 0.02707 0.01583 0.0097 0.9964 1.0000
2.500 0.1779 0.02844 0.01726 0.0012 0.9767 1.0000
2.750 0.2407 0.02976 0.01865 -0.0071 0.9563 1.0000
3.000 0.2915 0.03073 0.01975 -0.0127 0.9330 1.0000
3.250 0.3494 0.03163 0.02080 -0.0192 0.9096 1.0000
3.500 0.4035 0.03224 0.02161 -0.0244 0.8843 1.0000
3.750 0.4538 0.03266 0.02223 -0.0286 0.8580 1.0000
4.000 0.5199 0.03260 0.02247 -0.0346 0.8314 1.0000
4.250 0.5930 0.03167 0.02191 -0.0404 0.8035 1.0000
4.500 0.6443 0.03055 0.02108 -0.0416 0.7738 1.0000
4.750 0.6880 0.02920 0.02002 -0.0410 0.7430 1.0000
5.000 0.7204 0.02798 0.01898 -0.0383 0.7078 1.0000
5.250 0.7546 0.02625 0.01738 -0.0350 0.6685 1.0000
5.500 0.7815 0.02491 0.01607 -0.0310 0.6215 1.0000
5.750 0.8010 0.02426 0.01528 -0.0265 0.5636 1.0000
6.000 0.8175 0.02421 0.01486 -0.0222 0.4958 1.0000
6.250 0.8298 0.02497 0.01512 -0.0180 0.4208 1.0000
6.500 0.8399 0.02638 0.01594 -0.0142 0.3459 1.0000
6.750 0.8522 0.02815 0.01718 -0.0111 0.2835 1.0000
7.000 0.8697 0.02999 0.01866 -0.0091 0.2401 1.0000
7.250 0.8896 0.03181 0.02030 -0.0075 0.2107 1.0000
7.500 0.9115 0.03384 0.02242 -0.0062 0.1913 1.0000
7.750 0.9317 0.03581 0.02446 -0.0048 0.1762 1.0000
8.000 0.9553 0.03814 0.02672 -0.0040 0.1657 1.0000
8.250 0.9697 0.04052 0.02964 -0.0018 0.1580 1.0000
8.500 0.9886 0.04301 0.03216 -0.0006 0.1503 1.0000
8.750 0.9970 0.04597 0.03571 0.0021 0.1465 1.0000
9.000 1.0048 0.04917 0.03933 0.0046 0.1437 1.0000
9.250 1.0152 0.05211 0.04248 0.0066 0.1400 1.0000
9.500 1.0248 0.05555 0.04603 0.0084 0.1364 1.0000
9.750 1.0183 0.05927 0.05023 0.0117 0.1355 1.0000
10.000 1.0098 0.06334 0.05467 0.0148 0.1356 1.0000
10.250 1.0004 0.06767 0.05928 0.0174 0.1362 1.0000
10.500 0.9923 0.07223 0.06403 0.0195 0.1369 1.0000
10.750 0.9013 0.07826 0.07048 0.0241 0.1433 1.0000
11.000 0.8600 0.08558 0.07784 0.0227 0.1478 1.0000
11.250 0.8419 0.09228 0.08454 0.0208 0.1501 1.0000
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Polar data table (+)
Polar graphs
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