NACA 64A210 (naca64a210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64A210 (naca64a210-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.14 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64a210-il-1000000.txt Download as CSV file: xf-naca64a210-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6615 0.05062 0.04869 -0.0476 1.0000 0.0103
-8.750 -0.6829 0.04326 0.04105 -0.0462 1.0000 0.0096
-8.500 -0.7318 0.02588 0.02242 -0.0406 0.9972 0.0093
-8.250 -0.7071 0.02221 0.01830 -0.0418 0.9948 0.0097
-8.000 -0.6804 0.01984 0.01561 -0.0427 0.9921 0.0101
-7.750 -0.6511 0.01829 0.01382 -0.0437 0.9894 0.0105
-7.500 -0.6188 0.01755 0.01293 -0.0451 0.9873 0.0109
-7.250 -0.5911 0.01499 0.01010 -0.0461 0.9849 0.0119
-7.000 -0.5592 0.01444 0.00952 -0.0474 0.9824 0.0125
-6.750 -0.5314 0.01376 0.00877 -0.0477 0.9769 0.0130
-6.500 -0.5021 0.01304 0.00796 -0.0483 0.9724 0.0135
-6.250 -0.4745 0.01237 0.00721 -0.0485 0.9670 0.0141
-6.000 -0.4486 0.01184 0.00661 -0.0482 0.9599 0.0147
-5.750 -0.4218 0.01151 0.00622 -0.0480 0.9537 0.0151
-5.500 -0.4000 0.01041 0.00500 -0.0470 0.9454 0.0164
-5.250 -0.3749 0.00995 0.00449 -0.0466 0.9384 0.0173
-5.000 -0.3495 0.00960 0.00410 -0.0462 0.9308 0.0181
-4.750 -0.3236 0.00928 0.00373 -0.0458 0.9239 0.0191
-4.500 -0.2975 0.00900 0.00338 -0.0455 0.9164 0.0202
-4.250 -0.2710 0.00878 0.00312 -0.0452 0.9094 0.0211
-4.000 -0.2453 0.00834 0.00261 -0.0448 0.9017 0.0246
-3.750 -0.2185 0.00814 0.00237 -0.0446 0.8946 0.0275
-3.500 -0.1919 0.00787 0.00208 -0.0444 0.8870 0.0345
-3.250 -0.1651 0.00763 0.00187 -0.0442 0.8798 0.0498
-3.000 -0.1389 0.00731 0.00168 -0.0440 0.8718 0.0901
-2.750 -0.1138 0.00675 0.00147 -0.0438 0.8640 0.1916
-2.500 -0.0903 0.00597 0.00122 -0.0435 0.8560 0.3539
-2.250 -0.0658 0.00542 0.00110 -0.0431 0.8475 0.4902
-2.000 -0.0395 0.00522 0.00105 -0.0429 0.8395 0.5498
-1.750 -0.0125 0.00509 0.00101 -0.0427 0.8305 0.5906
-1.500 0.0147 0.00502 0.00097 -0.0426 0.8219 0.6169
-1.250 0.0420 0.00497 0.00094 -0.0425 0.8126 0.6393
-1.000 0.0692 0.00490 0.00093 -0.0423 0.8029 0.6680
-0.750 0.0961 0.00486 0.00093 -0.0421 0.7934 0.6967
-0.500 0.1234 0.00485 0.00093 -0.0419 0.7838 0.7149
-0.250 0.1510 0.00484 0.00093 -0.0418 0.7738 0.7296
0.000 0.1786 0.00485 0.00093 -0.0418 0.7642 0.7417
0.500 0.2339 0.00487 0.00095 -0.0417 0.7448 0.7630
0.750 0.2615 0.00489 0.00097 -0.0416 0.7351 0.7733
1.000 0.2889 0.00492 0.00099 -0.0415 0.7234 0.7838
1.500 0.3431 0.00497 0.00104 -0.0412 0.6931 0.8071
1.750 0.3697 0.00500 0.00107 -0.0409 0.6738 0.8199
2.000 0.3957 0.00507 0.00111 -0.0405 0.6485 0.8349
2.250 0.4214 0.00513 0.00116 -0.0401 0.6235 0.8539
2.500 0.4469 0.00517 0.00124 -0.0395 0.6006 0.8798
2.750 0.4719 0.00522 0.00133 -0.0388 0.5774 0.9144
3.000 0.5002 0.00539 0.00145 -0.0389 0.5396 0.9522
3.250 0.5346 0.00574 0.00159 -0.0406 0.4749 0.9759
3.500 0.5648 0.00675 0.00193 -0.0419 0.3156 0.9919
3.750 0.5945 0.00777 0.00235 -0.0432 0.1760 1.0000
4.000 0.6144 0.00842 0.00266 -0.0420 0.1013 1.0000
4.250 0.6365 0.00889 0.00294 -0.0410 0.0608 1.0000
4.500 0.6597 0.00929 0.00321 -0.0403 0.0379 1.0000
4.750 0.6835 0.00965 0.00353 -0.0396 0.0273 1.0000
5.000 0.7080 0.00997 0.00383 -0.0391 0.0228 1.0000
5.250 0.7318 0.01039 0.00429 -0.0384 0.0198 1.0000
5.500 0.7566 0.01070 0.00462 -0.0379 0.0186 1.0000
5.750 0.7811 0.01105 0.00500 -0.0374 0.0174 1.0000
6.000 0.8053 0.01145 0.00541 -0.0368 0.0165 1.0000
6.250 0.8279 0.01204 0.00605 -0.0360 0.0154 1.0000
6.500 0.8483 0.01290 0.00701 -0.0348 0.0145 1.0000
6.750 0.8725 0.01329 0.00743 -0.0343 0.0141 1.0000
7.000 0.8957 0.01383 0.00803 -0.0336 0.0136 1.0000
7.250 0.9182 0.01445 0.00870 -0.0328 0.0131 1.0000
7.500 0.9405 0.01511 0.00942 -0.0320 0.0127 1.0000
7.750 0.9627 0.01579 0.01015 -0.0312 0.0123 1.0000
8.000 0.9848 0.01648 0.01090 -0.0305 0.0119 1.0000
8.250 1.0071 0.01713 0.01158 -0.0298 0.0114 1.0000
8.500 1.0264 0.01829 0.01280 -0.0287 0.0108 1.0000
8.750 1.0425 0.02054 0.01525 -0.0271 0.0103 1.0000
9.000 1.0646 0.02117 0.01598 -0.0264 0.0101 1.0000
9.250 1.0854 0.02210 0.01704 -0.0255 0.0098 1.0000
9.500 1.1049 0.02329 0.01837 -0.0245 0.0095 1.0000
9.750 1.1230 0.02466 0.01991 -0.0233 0.0092 1.0000
10.000 1.1398 0.02612 0.02153 -0.0221 0.0090 1.0000
10.250 1.1559 0.02744 0.02300 -0.0208 0.0087 1.0000
10.500 1.1725 0.02837 0.02402 -0.0196 0.0084 1.0000
10.750 1.1885 0.02912 0.02486 -0.0184 0.0081 1.0000
11.000 1.2038 0.02983 0.02562 -0.0172 0.0079 1.0000
11.250 1.2138 0.03114 0.02702 -0.0154 0.0077 1.0000
11.500 1.2043 0.03460 0.03078 -0.0114 0.0074 1.0000
12.000 1.1645 0.04270 0.03957 -0.0038 0.0072 1.0000
12.250 1.1594 0.04522 0.04226 -0.0023 0.0071 1.0000
12.500 1.1478 0.04871 0.04596 -0.0013 0.0071 1.0000
12.750 1.1311 0.05319 0.05065 -0.0011 0.0070 1.0000
13.000 1.1091 0.05888 0.05655 -0.0023 0.0070 1.0000
13.250 1.0840 0.06581 0.06368 -0.0052 0.0070 1.0000
13.500 1.0531 0.07474 0.07280 -0.0101 0.0071 1.0000
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Polar data table (+)
Polar graphs
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