NACA 64-210 (naca64210-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64-210 (naca64210-il) Reynolds number: 50,000 Max Cl/Cd: 30.29 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64210-il-50000.txt Download as CSV file: xf-naca64210-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-210
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5253 0.12428 0.11709 0.0014 1.0000 0.2539
-10.250 -0.5335 0.12213 0.11502 0.0001 1.0000 0.2653
-10.000 -0.5343 0.11959 0.11252 -0.0004 1.0000 0.2787
-9.750 -0.5070 0.11414 0.10702 0.0013 1.0000 0.2977
-9.500 -0.4981 0.11077 0.10368 0.0018 1.0000 0.3160
-9.250 -0.4953 0.10791 0.10086 0.0019 1.0000 0.3335
-9.000 -0.5013 0.10580 0.09882 0.0020 1.0000 0.3505
-8.500 -0.4726 0.09777 0.09078 0.0031 1.0000 0.3840
-8.250 -0.4627 0.09446 0.08748 0.0036 1.0000 0.4009
-8.000 -0.4714 0.09288 0.08600 0.0046 1.0000 0.4222
-7.750 -0.4544 0.08870 0.08182 0.0050 1.0000 0.4389
-7.000 -0.5823 0.06145 0.05483 -0.0328 1.0000 0.2028
-6.750 -0.5860 0.05374 0.04640 -0.0372 1.0000 0.1608
-6.500 -0.5759 0.04874 0.04092 -0.0374 1.0000 0.1443
-6.250 -0.5637 0.04461 0.03609 -0.0368 1.0000 0.1327
-6.000 -0.5480 0.04099 0.03210 -0.0358 1.0000 0.1274
-5.750 -0.5307 0.03800 0.02824 -0.0344 1.0000 0.1219
-5.500 -0.5119 0.03521 0.02530 -0.0332 1.0000 0.1240
-5.250 -0.4923 0.03296 0.02279 -0.0320 1.0000 0.1275
-5.000 -0.4711 0.03081 0.02029 -0.0306 1.0000 0.1293
-4.750 -0.4488 0.02889 0.01805 -0.0291 1.0000 0.1318
-4.500 -0.4268 0.02714 0.01615 -0.0276 1.0000 0.1382
-4.250 -0.4053 0.02580 0.01470 -0.0260 1.0000 0.1492
-4.000 -0.3845 0.02433 0.01336 -0.0240 1.0000 0.1606
-3.750 -0.3659 0.02300 0.01212 -0.0221 1.0000 0.1812
-3.500 -0.3486 0.02143 0.01084 -0.0205 1.0000 0.2200
-3.250 -0.3504 0.01847 0.01069 -0.0142 1.0000 0.6192
-3.000 -0.1079 0.02269 0.01354 -0.0257 1.0000 0.9762
-2.750 -0.0500 0.02158 0.01206 -0.0334 1.0000 0.9942
-2.500 -0.0254 0.02097 0.01133 -0.0351 1.0000 1.0000
-2.250 -0.0241 0.02077 0.01112 -0.0326 1.0000 1.0000
-2.000 -0.0282 0.02067 0.01102 -0.0293 1.0000 1.0000
-1.750 -0.0369 0.02061 0.01097 -0.0253 1.0000 1.0000
-1.500 -0.0485 0.02056 0.01091 -0.0210 1.0000 1.0000
-1.250 -0.0617 0.02045 0.01080 -0.0166 1.0000 1.0000
-1.000 -0.0759 0.02028 0.01062 -0.0121 1.0000 1.0000
-0.750 -0.0902 0.02003 0.01035 -0.0076 1.0000 1.0000
-0.500 -0.1014 0.01976 0.01001 -0.0035 1.0000 1.0000
-0.250 -0.1015 0.01963 0.00978 -0.0011 1.0000 1.0000
0.000 -0.0899 0.01971 0.00973 -0.0004 1.0000 1.0000
0.250 -0.0733 0.01993 0.00982 -0.0005 1.0000 1.0000
0.500 -0.0545 0.02024 0.01000 -0.0008 1.0000 1.0000
0.750 -0.0348 0.02062 0.01027 -0.0011 1.0000 1.0000
1.000 -0.0149 0.02106 0.01060 -0.0015 1.0000 1.0000
1.250 0.0052 0.02154 0.01101 -0.0019 1.0000 1.0000
1.500 0.0254 0.02207 0.01148 -0.0023 1.0000 1.0000
1.750 0.0452 0.02265 0.01201 -0.0026 1.0000 1.0000
2.000 0.0767 0.02355 0.01290 -0.0052 0.9949 1.0000
2.250 0.1160 0.02464 0.01400 -0.0092 0.9852 1.0000
2.500 0.1530 0.02569 0.01509 -0.0127 0.9750 1.0000
2.750 0.1901 0.02678 0.01626 -0.0161 0.9645 1.0000
3.000 0.2290 0.02795 0.01752 -0.0198 0.9535 1.0000
3.250 0.2675 0.02910 0.01879 -0.0233 0.9418 1.0000
3.500 0.2998 0.03012 0.01997 -0.0257 0.9292 1.0000
3.750 0.3338 0.03120 0.02121 -0.0282 0.9158 1.0000
4.000 0.3704 0.03231 0.02252 -0.0310 0.9007 1.0000
4.250 0.4143 0.03344 0.02395 -0.0346 0.8831 1.0000
4.500 0.4461 0.03430 0.02507 -0.0360 0.8616 1.0000
4.750 0.4959 0.03488 0.02605 -0.0391 0.8333 1.0000
5.000 0.6736 0.02224 0.01479 -0.0342 0.6651 1.0000
5.250 0.6607 0.02192 0.01221 -0.0202 0.2805 1.0000
5.500 0.6654 0.02509 0.01429 -0.0172 0.1946 1.0000
5.750 0.6883 0.02727 0.01615 -0.0159 0.1637 1.0000
6.000 0.7194 0.02923 0.01804 -0.0155 0.1416 1.0000
6.250 0.7560 0.03163 0.02046 -0.0156 0.1307 1.0000
6.500 0.7866 0.03420 0.02305 -0.0155 0.1210 1.0000
6.750 0.8145 0.03679 0.02611 -0.0149 0.1168 1.0000
7.000 0.8403 0.03984 0.02958 -0.0141 0.1155 1.0000
7.250 0.8622 0.04311 0.03332 -0.0131 0.1150 1.0000
7.500 0.8808 0.04643 0.03704 -0.0121 0.1132 1.0000
7.750 0.8959 0.05005 0.04112 -0.0109 0.1129 1.0000
8.000 0.9040 0.05442 0.04614 -0.0094 0.1169 1.0000
8.250 0.9143 0.05923 0.05128 -0.0085 0.1212 1.0000
8.500 0.9079 0.06419 0.05696 -0.0073 0.1299 1.0000
8.750 0.9087 0.06975 0.06284 -0.0070 0.1396 1.0000
9.250 0.8631 0.08288 0.07656 -0.0096 0.1671 1.0000
9.500 0.8107 0.08971 0.08337 -0.0144 0.1706 1.0000
9.750 0.6872 0.11633 0.10958 -0.0491 0.3585 1.0000
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Polar data table (+)
Polar graphs
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