NACA 66-210 (naca66210-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66-210 (naca66210-il) Reynolds number: 50,000 Max Cl/Cd: 22.13 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca66210-il-50000.txt Download as CSV file: xf-naca66210-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-210
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4775 0.11310 0.10594 -0.0187 1.0000 0.2837
-9.750 -0.4757 0.11011 0.10300 -0.0183 1.0000 0.3002
-9.500 -0.4808 0.10775 0.10072 -0.0180 1.0000 0.3170
-9.250 -0.4698 0.10387 0.09686 -0.0169 1.0000 0.3355
-9.000 -0.4608 0.10080 0.09381 -0.0156 1.0000 0.3575
-8.750 -0.4520 0.09750 0.09054 -0.0141 1.0000 0.3811
-8.500 -0.4417 0.09454 0.08760 -0.0121 1.0000 0.4114
-8.250 -0.4321 0.09175 0.08484 -0.0101 1.0000 0.4420
-8.000 -0.4337 0.08992 0.08305 -0.0073 1.0000 0.4750
-7.750 -0.4216 0.08683 0.07998 -0.0055 1.0000 0.5035
-6.250 -0.5361 0.06994 0.06403 0.0023 1.0000 0.4367
-6.000 -0.5884 0.06776 0.06205 0.0053 1.0000 0.4330
-5.750 -0.6297 0.05289 0.04570 -0.0181 1.0000 0.1993
-5.500 -0.6135 0.04792 0.03982 -0.0181 1.0000 0.1575
-5.250 -0.5974 0.04441 0.03568 -0.0167 1.0000 0.1439
-5.000 -0.5802 0.04122 0.03203 -0.0153 1.0000 0.1381
-4.750 -0.5595 0.03869 0.02879 -0.0138 1.0000 0.1311
-4.500 -0.5378 0.03595 0.02567 -0.0125 1.0000 0.1266
-4.250 -0.5141 0.03363 0.02285 -0.0112 1.0000 0.1232
-4.000 -0.4898 0.03169 0.02046 -0.0100 1.0000 0.1229
-3.750 -0.4661 0.03012 0.01866 -0.0089 1.0000 0.1283
-3.500 -0.4407 0.02880 0.01698 -0.0077 1.0000 0.1328
-3.250 -0.1396 0.02435 0.01528 -0.0368 1.0000 1.0000
-3.000 -0.1361 0.02419 0.01488 -0.0338 1.0000 1.0000
-2.750 -0.1324 0.02404 0.01453 -0.0308 1.0000 1.0000
-2.500 -0.1283 0.02391 0.01417 -0.0278 1.0000 1.0000
-2.250 -0.1240 0.02378 0.01387 -0.0249 1.0000 1.0000
-2.000 -0.1193 0.02365 0.01359 -0.0219 1.0000 1.0000
-1.750 -0.1145 0.02353 0.01333 -0.0190 1.0000 1.0000
-1.500 -0.1095 0.02342 0.01308 -0.0161 1.0000 1.0000
-1.250 -0.1044 0.02331 0.01285 -0.0132 1.0000 1.0000
-1.000 -0.0992 0.02319 0.01262 -0.0102 1.0000 1.0000
-0.750 -0.0940 0.02308 0.01239 -0.0073 1.0000 1.0000
-0.500 -0.0887 0.02296 0.01218 -0.0044 1.0000 1.0000
-0.250 -0.0833 0.02284 0.01198 -0.0015 1.0000 1.0000
0.000 -0.0775 0.02273 0.01179 0.0014 1.0000 1.0000
0.250 -0.0712 0.02264 0.01162 0.0042 1.0000 1.0000
0.500 -0.0639 0.02256 0.01148 0.0068 1.0000 1.0000
0.750 -0.0550 0.02254 0.01137 0.0091 1.0000 1.0000
1.000 -0.0436 0.02258 0.01135 0.0110 1.0000 1.0000
1.250 -0.0297 0.02270 0.01141 0.0124 1.0000 1.0000
1.500 -0.0141 0.02289 0.01155 0.0135 1.0000 1.0000
1.750 0.0028 0.02314 0.01177 0.0143 1.0000 1.0000
2.000 0.0206 0.02344 0.01205 0.0149 1.0000 1.0000
2.250 0.0388 0.02380 0.01241 0.0154 1.0000 1.0000
2.500 0.0575 0.02420 0.01282 0.0158 1.0000 1.0000
2.750 0.0762 0.02466 0.01331 0.0161 1.0000 1.0000
3.000 0.0949 0.02516 0.01388 0.0163 1.0000 1.0000
3.250 0.1136 0.02572 0.01450 0.0165 1.0000 1.0000
3.500 0.1321 0.02633 0.01519 0.0166 1.0000 1.0000
3.750 0.1504 0.02700 0.01595 0.0167 1.0000 1.0000
4.000 0.1684 0.02773 0.01680 0.0168 1.0000 1.0000
4.250 0.1859 0.02853 0.01772 0.0167 1.0000 1.0000
4.500 0.2030 0.02941 0.01878 0.0167 1.0000 1.0000
4.750 0.2194 0.03037 0.01990 0.0165 1.0000 1.0000
5.000 0.2786 0.03284 0.02279 0.0080 0.9755 1.0000
5.250 0.3483 0.03520 0.02574 -0.0013 0.9379 1.0000
5.500 0.6105 0.02781 0.01610 -0.0065 0.1443 1.0000
5.750 0.6683 0.03020 0.01839 -0.0102 0.1253 1.0000
6.000 0.7153 0.03295 0.02140 -0.0121 0.1205 1.0000
6.250 0.7452 0.03530 0.02413 -0.0117 0.1165 1.0000
6.500 0.7716 0.03794 0.02691 -0.0113 0.1116 1.0000
6.750 0.7941 0.04070 0.03021 -0.0098 0.1127 1.0000
7.000 0.8126 0.04392 0.03405 -0.0078 0.1163 1.0000
7.250 0.8294 0.04756 0.03812 -0.0060 0.1205 1.0000
7.500 0.8411 0.05105 0.04228 -0.0035 0.1278 1.0000
7.750 0.8518 0.05549 0.04715 -0.0017 0.1351 1.0000
8.000 0.8525 0.05973 0.05205 0.0008 0.1472 1.0000
8.250 0.8548 0.06495 0.05770 0.0022 0.1630 1.0000
8.500 0.8457 0.07256 0.06586 0.0017 0.2064 1.0000
8.750 0.7860 0.07848 0.07212 0.0004 0.2386 1.0000
9.000 0.7347 0.08633 0.07991 -0.0049 0.2665 1.0000
9.250 0.6514 0.07894 0.07282 0.0068 0.2103 1.0000
9.500 0.6320 0.10676 0.09988 -0.0286 0.4084 1.0000
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Polar data table (+)
Polar graphs
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