NACA 64-210 (naca64210-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64-210 (naca64210-il) Reynolds number: 100,000 Max Cl/Cd: 46.36 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64210-il-100000.txt Download as CSV file: xf-naca64210-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4526 0.09156 0.08694 -0.0215 1.0000 0.1337
-9.250 -0.4493 0.08693 0.08235 -0.0217 1.0000 0.1384
-9.000 -0.5377 0.09046 0.08559 -0.0205 1.0000 0.1292
-8.750 -0.5578 0.08544 0.08070 -0.0267 1.0000 0.1335
-8.500 -0.5464 0.08221 0.07748 -0.0247 1.0000 0.1413
-8.250 -0.5640 0.07745 0.07282 -0.0293 1.0000 0.1461
-8.000 -0.6005 0.07247 0.06773 -0.0361 1.0000 0.1487
-7.750 -0.5823 0.06924 0.06462 -0.0337 1.0000 0.1612
-7.500 -0.5758 0.06596 0.06138 -0.0328 1.0000 0.1722
-7.250 -0.5767 0.06242 0.05784 -0.0330 1.0000 0.1844
-7.000 -0.5753 0.05920 0.05460 -0.0327 1.0000 0.1986
-6.750 -0.5713 0.05639 0.05178 -0.0317 1.0000 0.2154
-6.250 -0.5615 0.03954 0.03255 -0.0356 1.0000 0.0917
-6.000 -0.5454 0.03498 0.02743 -0.0335 1.0000 0.0770
-5.750 -0.5297 0.03178 0.02395 -0.0319 1.0000 0.0733
-5.500 -0.5131 0.02951 0.02132 -0.0301 1.0000 0.0734
-5.250 -0.4953 0.02760 0.01907 -0.0284 1.0000 0.0744
-5.000 -0.4759 0.02565 0.01679 -0.0268 1.0000 0.0740
-4.750 -0.4559 0.02398 0.01487 -0.0252 1.0000 0.0745
-4.500 -0.4355 0.02260 0.01330 -0.0237 1.0000 0.0762
-4.250 -0.4156 0.02139 0.01195 -0.0224 1.0000 0.0807
-4.000 -0.3962 0.02020 0.01086 -0.0211 1.0000 0.0859
-3.750 -0.3764 0.01929 0.00989 -0.0198 1.0000 0.0913
-3.500 -0.3576 0.01829 0.00903 -0.0186 1.0000 0.1003
-3.250 -0.3384 0.01749 0.00830 -0.0176 1.0000 0.1157
-3.000 -0.3179 0.01643 0.00746 -0.0170 1.0000 0.1523
-2.750 -0.3112 0.01410 0.00776 -0.0129 1.0000 0.6738
-2.500 -0.3004 0.01448 0.00820 -0.0089 0.9997 0.7349
-2.250 -0.2708 0.01512 0.00880 -0.0080 0.9900 0.7870
-2.000 -0.2533 0.01590 0.00966 -0.0035 0.9798 0.8405
-1.750 -0.2391 0.01658 0.01037 0.0024 0.9702 0.8912
-1.500 -0.2083 0.01675 0.01040 0.0025 0.9613 0.9170
-1.250 -0.1579 0.01689 0.01036 -0.0023 0.9558 0.9305
-1.000 -0.1127 0.01691 0.01024 -0.0063 0.9480 0.9427
-0.750 -0.0526 0.01701 0.01018 -0.0132 0.9435 0.9510
-0.500 0.0034 0.01706 0.01013 -0.0194 0.9381 0.9600
-0.250 0.0638 0.01706 0.01005 -0.0265 0.9327 0.9677
0.000 0.1293 0.01702 0.00995 -0.0346 0.9291 0.9736
0.250 0.1913 0.01694 0.00985 -0.0421 0.9248 0.9805
0.500 0.2486 0.01680 0.00973 -0.0487 0.9183 0.9884
0.750 0.3100 0.01659 0.00955 -0.0560 0.9138 0.9953
1.000 0.3482 0.01657 0.00959 -0.0591 0.9041 1.0000
1.250 0.3752 0.01661 0.00966 -0.0600 0.8939 1.0000
1.500 0.4029 0.01662 0.00972 -0.0607 0.8844 1.0000
1.750 0.4170 0.01684 0.00998 -0.0591 0.8720 1.0000
2.000 0.4312 0.01706 0.01028 -0.0573 0.8600 1.0000
2.250 0.4480 0.01726 0.01052 -0.0557 0.8488 1.0000
2.500 0.4742 0.01730 0.01063 -0.0554 0.8402 1.0000
2.750 0.4874 0.01763 0.01102 -0.0532 0.8280 1.0000
3.000 0.5069 0.01788 0.01137 -0.0518 0.8163 1.0000
3.250 0.5326 0.01779 0.01138 -0.0507 0.8026 1.0000
3.500 0.5625 0.01673 0.01037 -0.0479 0.7799 1.0000
3.750 0.5838 0.01545 0.00904 -0.0431 0.7423 1.0000
4.000 0.6066 0.01469 0.00826 -0.0398 0.7091 1.0000
4.250 0.6284 0.01439 0.00804 -0.0374 0.6759 1.0000
4.500 0.6481 0.01398 0.00759 -0.0343 0.6157 1.0000
4.750 0.6470 0.01532 0.00720 -0.0278 0.2740 1.0000
5.000 0.6509 0.01834 0.00891 -0.0248 0.1222 1.0000
5.250 0.6689 0.01972 0.01021 -0.0232 0.1010 1.0000
5.500 0.6887 0.02109 0.01149 -0.0219 0.0885 1.0000
5.750 0.7112 0.02275 0.01299 -0.0211 0.0804 1.0000
6.000 0.7382 0.02432 0.01462 -0.0205 0.0753 1.0000
6.250 0.7654 0.02632 0.01652 -0.0204 0.0704 1.0000
6.500 0.7926 0.02834 0.01878 -0.0200 0.0666 1.0000
6.750 0.8198 0.03063 0.02136 -0.0195 0.0655 1.0000
7.000 0.8452 0.03331 0.02442 -0.0187 0.0654 1.0000
7.250 0.8683 0.03647 0.02796 -0.0177 0.0664 1.0000
7.500 0.8882 0.03969 0.03161 -0.0166 0.0666 1.0000
7.750 0.9051 0.04302 0.03538 -0.0153 0.0666 1.0000
8.000 0.9244 0.04881 0.04129 -0.0151 0.0694 1.0000
9.750 0.8310 0.09423 0.08982 -0.0160 0.1643 1.0000
10.000 0.7732 0.10326 0.09871 -0.0279 0.1577 1.0000
10.250 0.8236 0.10407 0.09962 -0.0190 0.1507 1.0000
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Polar data table (+)
Polar graphs
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