NACA 64A210 (naca64a210-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64A210 (naca64a210-il) Reynolds number: 50,000 Max Cl/Cd: 33.69 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64a210-il-50000.txt Download as CSV file: xf-naca64a210-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64A210
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 -0.4979 0.10625 0.09924 -0.0007 1.0000 0.3256
-8.750 -0.4941 0.10322 0.09625 -0.0002 1.0000 0.3436
-8.500 -0.5080 0.10166 0.09480 -0.0001 1.0000 0.3619
-8.250 -0.4823 0.09667 0.08977 0.0012 1.0000 0.3802
-8.000 -0.4737 0.09351 0.08664 0.0022 1.0000 0.4006
-7.750 -0.4697 0.09052 0.08369 0.0032 1.0000 0.4220
-7.500 -0.4739 0.08871 0.08197 0.0050 1.0000 0.4476
-7.250 -0.4478 0.08399 0.07721 0.0056 1.0000 0.4669
-6.500 -0.5729 0.05446 0.04726 -0.0358 1.0000 0.1680
-6.250 -0.5663 0.04918 0.04123 -0.0359 1.0000 0.1437
-6.000 -0.5547 0.04516 0.03648 -0.0346 1.0000 0.1312
-5.750 -0.5391 0.04157 0.03264 -0.0333 1.0000 0.1264
-5.500 -0.5226 0.03843 0.02892 -0.0319 1.0000 0.1229
-5.250 -0.5042 0.03590 0.02601 -0.0305 1.0000 0.1246
-5.000 -0.4837 0.03353 0.02323 -0.0292 1.0000 0.1262
-4.750 -0.4610 0.03127 0.02056 -0.0279 1.0000 0.1269
-4.500 -0.4370 0.02929 0.01822 -0.0267 1.0000 0.1294
-4.250 -0.4132 0.02748 0.01628 -0.0256 1.0000 0.1375
-4.000 -0.3886 0.02593 0.01460 -0.0244 1.0000 0.1486
-3.750 -0.3643 0.02443 0.01313 -0.0230 1.0000 0.1628
-3.500 -0.3417 0.02289 0.01180 -0.0219 1.0000 0.1935
-3.250 -0.3217 0.02027 0.01013 -0.0210 1.0000 0.2938
-3.000 -0.0733 0.02109 0.01165 -0.0395 1.0000 1.0000
-2.750 -0.0707 0.02070 0.01119 -0.0372 1.0000 1.0000
-2.500 -0.0714 0.02037 0.01081 -0.0342 1.0000 1.0000
-2.250 -0.0760 0.02008 0.01049 -0.0307 1.0000 1.0000
-2.000 -0.0844 0.01982 0.01019 -0.0265 1.0000 1.0000
-1.750 -0.0959 0.01954 0.00990 -0.0219 1.0000 1.0000
-1.500 -0.1089 0.01925 0.00958 -0.0170 1.0000 1.0000
-1.250 -0.1179 0.01900 0.00926 -0.0127 1.0000 1.0000
-1.000 -0.1143 0.01892 0.00903 -0.0103 1.0000 1.0000
-0.750 -0.1015 0.01900 0.00891 -0.0093 1.0000 1.0000
-0.500 -0.0847 0.01918 0.00891 -0.0089 1.0000 1.0000
-0.250 -0.0662 0.01944 0.00901 -0.0087 1.0000 1.0000
0.000 -0.0468 0.01976 0.00918 -0.0086 1.0000 1.0000
0.250 -0.0269 0.02012 0.00942 -0.0086 1.0000 1.0000
0.500 -0.0068 0.02054 0.00972 -0.0086 1.0000 1.0000
0.750 0.0134 0.02099 0.01008 -0.0087 1.0000 1.0000
1.000 0.0336 0.02149 0.01051 -0.0088 1.0000 1.0000
1.250 0.0538 0.02203 0.01100 -0.0089 1.0000 1.0000
1.500 0.0739 0.02262 0.01154 -0.0091 1.0000 1.0000
1.750 0.0939 0.02324 0.01214 -0.0093 1.0000 1.0000
2.000 0.1138 0.02391 0.01279 -0.0095 1.0000 1.0000
2.250 0.1335 0.02462 0.01351 -0.0098 1.0000 1.0000
2.500 0.1530 0.02538 0.01430 -0.0100 1.0000 1.0000
2.750 0.1748 0.02622 0.01518 -0.0108 0.9988 1.0000
3.000 0.2194 0.02753 0.01659 -0.0160 0.9871 1.0000
3.250 0.2620 0.02881 0.01800 -0.0206 0.9747 1.0000
3.500 0.3030 0.03006 0.01943 -0.0248 0.9612 1.0000
3.750 0.3437 0.03129 0.02084 -0.0288 0.9464 1.0000
4.000 0.3858 0.03250 0.02228 -0.0329 0.9302 1.0000
4.250 0.4340 0.03371 0.02381 -0.0376 0.9122 1.0000
4.500 0.4668 0.03461 0.02497 -0.0394 0.8907 1.0000
4.750 0.5162 0.03526 0.02605 -0.0430 0.8631 1.0000
5.000 0.6768 0.02660 0.01873 -0.0461 0.7524 1.0000
5.250 0.7059 0.02095 0.01321 -0.0320 0.5801 1.0000
5.500 0.6897 0.02423 0.01353 -0.0224 0.2324 1.0000
5.750 0.7033 0.02685 0.01554 -0.0200 0.1777 1.0000
6.000 0.7329 0.02907 0.01756 -0.0193 0.1496 1.0000
6.250 0.7670 0.03131 0.01967 -0.0194 0.1310 1.0000
6.500 0.8018 0.03391 0.02248 -0.0195 0.1223 1.0000
6.750 0.8324 0.03666 0.02539 -0.0192 0.1170 1.0000
7.000 0.8570 0.03967 0.02871 -0.0184 0.1123 1.0000
7.250 0.8781 0.04259 0.03216 -0.0170 0.1098 1.0000
7.500 0.8977 0.04613 0.03618 -0.0156 0.1105 1.0000
7.750 0.9145 0.05003 0.04055 -0.0142 0.1123 1.0000
8.000 0.9335 0.05481 0.04549 -0.0134 0.1144 1.0000
8.250 0.9281 0.05852 0.05037 -0.0101 0.1220 1.0000
8.500 0.9356 0.06339 0.05552 -0.0089 0.1260 1.0000
8.750 0.9227 0.06863 0.06142 -0.0073 0.1358 1.0000
9.000 0.8305 0.06359 0.05699 0.0016 0.1387 1.0000
9.250 0.8041 0.06896 0.06254 0.0030 0.1450 1.0000
9.500 0.7598 0.07468 0.06833 0.0031 0.1471 1.0000
9.750 0.7207 0.08202 0.07569 0.0003 0.1510 1.0000
10.000 0.6759 0.09245 0.08607 -0.0065 0.1615 1.0000
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Polar data table (+)
Polar graphs
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