NACA 66-210 (naca66210-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66-210 (naca66210-il) Reynolds number: 100,000 Max Cl/Cd: 32.84 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca66210-il-100000.txt Download as CSV file: xf-naca66210-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3960 0.10661 0.10180 -0.0342 1.0000 0.0991
-10.500 -0.4055 0.10295 0.09821 -0.0367 1.0000 0.1030
-10.250 -0.4282 0.09916 0.09451 -0.0411 1.0000 0.1044
-10.000 -0.4067 0.09460 0.08991 -0.0381 1.0000 0.1087
-9.750 -0.4053 0.09106 0.08639 -0.0383 1.0000 0.1140
-9.500 -0.4247 0.08685 0.08226 -0.0417 1.0000 0.1176
-9.250 -0.4529 0.08212 0.07767 -0.0462 1.0000 0.1184
-9.000 -0.4213 0.07899 0.07447 -0.0406 1.0000 0.1263
-8.750 -0.4398 0.07484 0.07042 -0.0424 1.0000 0.1302
-8.500 -0.4693 0.07079 0.06647 -0.0439 1.0000 0.1311
-8.250 -0.4967 0.06827 0.06406 -0.0416 1.0000 0.1311
-8.000 -0.5251 0.06657 0.06243 -0.0374 1.0000 0.1310
-7.750 -0.5549 0.06468 0.06056 -0.0336 1.0000 0.1314
-7.500 -0.6197 0.06989 0.06539 -0.0321 1.0000 0.1252
-7.250 -0.6345 0.06792 0.06334 -0.0291 1.0000 0.1297
-6.750 -0.6483 0.06262 0.05795 -0.0237 1.0000 0.1417
-5.750 -0.6505 0.05220 0.04717 -0.0145 1.0000 0.1939
-4.500 -0.5510 0.03259 0.02440 -0.0086 1.0000 0.0856
-4.250 -0.5252 0.03028 0.02138 -0.0068 1.0000 0.0752
-4.000 -0.5019 0.02809 0.01889 -0.0057 1.0000 0.0737
-3.750 -0.4790 0.02679 0.01722 -0.0045 1.0000 0.0755
-3.500 -0.4554 0.02536 0.01554 -0.0035 1.0000 0.0759
-3.250 -0.4320 0.02409 0.01409 -0.0024 1.0000 0.0764
-3.000 -0.4090 0.02274 0.01269 -0.0013 1.0000 0.0780
-2.750 -0.3878 0.02162 0.01170 -0.0004 1.0000 0.0839
-2.500 -0.3664 0.02096 0.01099 0.0007 1.0000 0.0903
-2.250 -0.3462 0.02002 0.01012 0.0019 1.0000 0.0968
-2.000 -0.3252 0.01936 0.00947 0.0029 1.0000 0.1104
-1.750 -0.1167 0.02041 0.01336 -0.0185 1.0000 1.0000
-1.500 -0.1114 0.02030 0.01315 -0.0157 1.0000 1.0000
-1.250 -0.1061 0.02018 0.01294 -0.0130 1.0000 1.0000
-1.000 -0.1008 0.02006 0.01274 -0.0101 1.0000 1.0000
-0.750 -0.0956 0.01994 0.01252 -0.0073 1.0000 1.0000
-0.500 -0.0907 0.01980 0.01232 -0.0044 1.0000 1.0000
-0.250 -0.0862 0.01966 0.01211 -0.0014 1.0000 1.0000
0.000 -0.0819 0.01949 0.01189 0.0016 1.0000 1.0000
0.250 -0.0778 0.01931 0.01167 0.0047 1.0000 1.0000
0.500 -0.0510 0.01955 0.01184 0.0035 0.9957 1.0000
0.750 -0.0230 0.01982 0.01205 0.0020 0.9903 1.0000
1.000 0.0073 0.02022 0.01242 0.0002 0.9846 1.0000
1.250 0.0325 0.02049 0.01266 -0.0006 0.9782 1.0000
1.500 0.0635 0.02094 0.01311 -0.0024 0.9717 1.0000
1.750 0.0885 0.02126 0.01342 -0.0031 0.9641 1.0000
2.000 0.1236 0.02183 0.01402 -0.0056 0.9572 1.0000
2.250 0.1484 0.02214 0.01436 -0.0061 0.9482 1.0000
2.500 0.1854 0.02275 0.01504 -0.0088 0.9404 1.0000
2.750 0.2170 0.02317 0.01553 -0.0104 0.9306 1.0000
3.000 0.2478 0.02359 0.01603 -0.0117 0.9197 1.0000
3.250 0.2838 0.02405 0.01665 -0.0139 0.9089 1.0000
3.500 0.3257 0.02448 0.01724 -0.0169 0.8975 1.0000
3.750 0.3671 0.02465 0.01761 -0.0194 0.8820 1.0000
4.000 0.5930 0.01806 0.00821 -0.0341 0.1229 1.0000
4.250 0.5999 0.01891 0.00902 -0.0304 0.1028 1.0000
4.500 0.6060 0.01972 0.00980 -0.0265 0.0917 1.0000
4.750 0.6133 0.02051 0.01058 -0.0229 0.0859 1.0000
5.000 0.6243 0.02176 0.01171 -0.0199 0.0815 1.0000
5.250 0.6429 0.02276 0.01277 -0.0180 0.0766 1.0000
5.500 0.6657 0.02424 0.01413 -0.0172 0.0705 1.0000
5.750 0.6983 0.02661 0.01656 -0.0178 0.0686 1.0000
6.000 0.7252 0.02857 0.01873 -0.0171 0.0681 1.0000
6.250 0.7509 0.03097 0.02139 -0.0163 0.0683 1.0000
6.500 0.7713 0.03280 0.02360 -0.0146 0.0671 1.0000
6.750 0.7921 0.03533 0.02648 -0.0132 0.0672 1.0000
7.000 0.8161 0.03839 0.02982 -0.0121 0.0704 1.0000
7.250 0.8340 0.04430 0.03717 -0.0072 0.1058 1.0000
8.750 0.8828 0.07540 0.07031 0.0015 0.1649 1.0000
9.000 0.8387 0.07661 0.07194 0.0046 0.1635 1.0000
9.250 0.8025 0.07977 0.07519 0.0062 0.1618 1.0000
9.500 0.7723 0.08420 0.07965 0.0054 0.1604 1.0000
9.750 0.8377 0.08846 0.08379 0.0074 0.1367 1.0000
10.000 0.8029 0.09167 0.08707 0.0080 0.1364 1.0000
10.250 0.7692 0.09664 0.09206 0.0051 0.1361 1.0000
10.500 0.7359 0.10394 0.09929 -0.0021 0.1354 1.0000
10.750 0.7139 0.11034 0.10559 -0.0084 0.1322 1.0000
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Polar data table (+)
Polar graphs
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