NACA 64-210 (naca64210-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-210 (naca64210-il) Reynolds number: 500,000 Max Cl/Cd: 63.2 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64210-il-500000-n5.txt Download as CSV file: xf-naca64210-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6176 0.09870 0.09637 -0.0141 1.0000 0.0079
-11.250 -0.6442 0.08740 0.08512 -0.0202 1.0000 0.0080
-10.250 -0.8560 0.03394 0.03043 -0.0427 1.0000 0.0077
-10.000 -0.8576 0.02952 0.02547 -0.0411 1.0000 0.0080
-9.750 -0.8501 0.02640 0.02196 -0.0399 1.0000 0.0082
-9.500 -0.8336 0.02495 0.02034 -0.0391 1.0000 0.0085
-9.250 -0.8141 0.02401 0.01930 -0.0385 1.0000 0.0088
-9.000 -0.7944 0.02304 0.01820 -0.0379 1.0000 0.0091
-8.750 -0.7738 0.02222 0.01725 -0.0372 1.0000 0.0095
-8.500 -0.7536 0.02126 0.01615 -0.0365 1.0000 0.0100
-8.250 -0.7341 0.02012 0.01482 -0.0355 1.0000 0.0106
-8.000 -0.7099 0.01909 0.01361 -0.0354 0.9973 0.0111
-7.750 -0.6790 0.01804 0.01237 -0.0367 0.9896 0.0114
-7.500 -0.6493 0.01660 0.01079 -0.0379 0.9813 0.0122
-7.250 -0.6173 0.01587 0.00998 -0.0394 0.9731 0.0127
-7.000 -0.5851 0.01532 0.00935 -0.0407 0.9642 0.0134
-6.750 -0.5542 0.01474 0.00870 -0.0417 0.9541 0.0143
-6.500 -0.5249 0.01416 0.00802 -0.0424 0.9431 0.0150
-6.250 -0.4975 0.01357 0.00731 -0.0425 0.9313 0.0156
-6.000 -0.4714 0.01308 0.00671 -0.0423 0.9194 0.0159
-5.750 -0.4475 0.01229 0.00584 -0.0418 0.9071 0.0170
-5.500 -0.4221 0.01192 0.00542 -0.0415 0.8956 0.0181
-5.250 -0.3963 0.01159 0.00503 -0.0413 0.8845 0.0192
-5.000 -0.3706 0.01123 0.00457 -0.0409 0.8742 0.0204
-4.750 -0.3446 0.01091 0.00417 -0.0407 0.8636 0.0215
-4.500 -0.3182 0.01062 0.00380 -0.0405 0.8533 0.0227
-4.250 -0.2920 0.01024 0.00337 -0.0403 0.8436 0.0255
-3.750 -0.2380 0.00985 0.00284 -0.0401 0.8244 0.0312
-3.500 -0.2111 0.00959 0.00256 -0.0400 0.8153 0.0376
-3.250 -0.1838 0.00941 0.00234 -0.0399 0.8062 0.0442
-3.000 -0.1567 0.00913 0.00213 -0.0399 0.7974 0.0665
-2.750 -0.1302 0.00870 0.00190 -0.0400 0.7886 0.1306
-2.500 -0.1043 0.00797 0.00162 -0.0402 0.7793 0.2629
-2.250 -0.0787 0.00721 0.00139 -0.0404 0.7706 0.4228
-2.000 -0.0515 0.00696 0.00132 -0.0404 0.7621 0.4909
-1.750 -0.0242 0.00677 0.00128 -0.0404 0.7537 0.5489
-1.500 0.0028 0.00660 0.00130 -0.0403 0.7456 0.6108
-1.250 0.0303 0.00654 0.00130 -0.0402 0.7368 0.6466
-1.000 0.0582 0.00652 0.00128 -0.0401 0.7284 0.6614
-0.750 0.0864 0.00652 0.00126 -0.0402 0.7199 0.6709
-0.500 0.1146 0.00652 0.00124 -0.0402 0.7122 0.6786
-0.250 0.1428 0.00653 0.00123 -0.0403 0.7044 0.6868
0.000 0.1710 0.00654 0.00124 -0.0404 0.6967 0.6950
0.250 0.1992 0.00657 0.00124 -0.0404 0.6888 0.7037
0.500 0.2274 0.00657 0.00127 -0.0405 0.6808 0.7116
1.000 0.2837 0.00662 0.00135 -0.0406 0.6662 0.7287
1.250 0.3116 0.00666 0.00140 -0.0406 0.6580 0.7377
1.500 0.3396 0.00670 0.00145 -0.0406 0.6475 0.7471
1.750 0.3672 0.00675 0.00151 -0.0405 0.6337 0.7559
2.000 0.3942 0.00684 0.00157 -0.0403 0.6081 0.7649
2.250 0.4202 0.00701 0.00162 -0.0399 0.5683 0.7742
2.500 0.4463 0.00721 0.00170 -0.0396 0.5276 0.7836
2.750 0.4721 0.00747 0.00182 -0.0393 0.4772 0.7936
3.250 0.5181 0.00879 0.00238 -0.0381 0.2709 0.8133
3.500 0.5407 0.00958 0.00277 -0.0376 0.1696 0.8235
3.750 0.5635 0.01030 0.00316 -0.0371 0.0876 0.8345
4.000 0.5878 0.01075 0.00348 -0.0366 0.0511 0.8452
4.250 0.6129 0.01105 0.00377 -0.0362 0.0393 0.8564
4.500 0.6381 0.01130 0.00406 -0.0357 0.0333 0.8681
4.750 0.6626 0.01159 0.00439 -0.0352 0.0284 0.8807
5.250 0.7104 0.01213 0.00507 -0.0337 0.0227 0.9092
5.500 0.7332 0.01243 0.00542 -0.0327 0.0205 0.9261
5.750 0.7552 0.01291 0.00595 -0.0317 0.0184 0.9468
6.250 0.8109 0.01374 0.00694 -0.0323 0.0167 1.0000
6.500 0.8356 0.01426 0.00750 -0.0320 0.0158 1.0000
6.750 0.8599 0.01481 0.00809 -0.0316 0.0152 1.0000
7.000 0.8841 0.01534 0.00867 -0.0313 0.0145 1.0000
7.250 0.9073 0.01598 0.00934 -0.0308 0.0137 1.0000
7.500 0.9275 0.01707 0.01049 -0.0299 0.0130 1.0000
7.750 0.9503 0.01777 0.01127 -0.0294 0.0128 1.0000
8.000 0.9725 0.01856 0.01215 -0.0287 0.0126 1.0000
8.250 0.9945 0.01941 0.01312 -0.0281 0.0123 1.0000
8.500 1.0162 0.02028 0.01408 -0.0274 0.0119 1.0000
8.750 1.0382 0.02106 0.01496 -0.0268 0.0113 1.0000
9.000 1.0598 0.02182 0.01581 -0.0262 0.0109 1.0000
9.250 1.0807 0.02263 0.01670 -0.0256 0.0105 1.0000
9.500 1.1008 0.02355 0.01771 -0.0248 0.0102 1.0000
9.750 1.1201 0.02447 0.01873 -0.0240 0.0099 1.0000
10.000 1.1372 0.02571 0.02011 -0.0230 0.0095 1.0000
10.250 1.1492 0.02794 0.02255 -0.0215 0.0092 1.0000
10.500 1.1649 0.02919 0.02399 -0.0203 0.0090 1.0000
10.750 1.1789 0.03052 0.02552 -0.0189 0.0087 1.0000
11.000 1.1896 0.03212 0.02734 -0.0173 0.0084 1.0000
11.250 1.1958 0.03374 0.02916 -0.0151 0.0081 1.0000
11.500 1.1986 0.03548 0.03110 -0.0127 0.0078 1.0000
11.750 1.1981 0.03754 0.03336 -0.0104 0.0076 1.0000
12.000 1.1948 0.03990 0.03593 -0.0083 0.0075 1.0000
12.250 1.1930 0.04208 0.03828 -0.0069 0.0073 1.0000
12.500 1.1868 0.04494 0.04133 -0.0058 0.0072 1.0000
12.750 1.1804 0.04796 0.04452 -0.0053 0.0071 1.0000
13.000 1.1719 0.05146 0.04819 -0.0054 0.0070 1.0000
13.250 1.1572 0.05612 0.05305 -0.0063 0.0070 1.0000
13.500 1.1471 0.06047 0.05757 -0.0079 0.0069 1.0000
13.750 1.1278 0.06673 0.06400 -0.0108 0.0069 1.0000
14.000 1.0727 0.08079 0.07844 -0.0190 0.0070 1.0000
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Polar data table (+)
Polar graphs
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