NACA 0012-64 a=0.8 c(li)=0.2 (naca001264a08cli02-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0012-64 a=0.8 c(li)=0.2 (naca001264a08cli02-il) Reynolds number: 50,000 Max Cl/Cd: 33.04 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001264a08cli02-il-50000.txt Download as CSV file: xf-naca001264a08cli02-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0012-64 a=0.8 c(li)=0.2
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4561 0.11087 0.10380 -0.0158 1.0000 0.3338
-9.250 -0.4615 0.10848 0.10149 -0.0146 1.0000 0.3508
-9.000 -0.4645 0.10570 0.09880 -0.0132 1.0000 0.3681
-8.750 -0.4409 0.10141 0.09449 -0.0115 1.0000 0.3907
-8.500 -0.4500 0.09939 0.09257 -0.0092 1.0000 0.4128
-8.250 -0.4410 0.09655 0.08976 -0.0069 1.0000 0.4395
-8.000 -0.4279 0.09334 0.08659 -0.0046 1.0000 0.4682
-7.750 -0.4297 0.09143 0.08475 -0.0011 1.0000 0.5000
-7.500 -0.3963 0.08696 0.08023 0.0000 1.0000 0.5361
-7.250 -0.3844 0.08399 0.07730 0.0021 1.0000 0.5665
-6.000 -0.4625 0.07110 0.06502 0.0132 1.0000 0.5410
-5.750 -0.5162 0.06898 0.06313 0.0186 1.0000 0.5192
-5.500 -0.5696 0.06559 0.05994 0.0208 1.0000 0.4884
-5.250 -0.6237 0.05982 0.05405 0.0157 1.0000 0.4255
-5.000 -0.6078 0.04914 0.04137 -0.0001 1.0000 0.2178
-4.750 -0.5859 0.04500 0.03635 0.0011 1.0000 0.1743
-4.500 -0.5636 0.04220 0.03271 0.0032 1.0000 0.1485
-4.250 -0.5415 0.03967 0.02959 0.0052 1.0000 0.1346
-4.000 -0.5186 0.03756 0.02680 0.0072 1.0000 0.1240
-3.750 -0.4941 0.03529 0.02427 0.0084 1.0000 0.1196
-3.500 -0.4688 0.03347 0.02210 0.0095 1.0000 0.1182
-3.250 -0.4423 0.03189 0.02023 0.0104 1.0000 0.1178
-3.000 -0.4133 0.03041 0.01851 0.0111 1.0000 0.1163
-2.750 -0.3820 0.02913 0.01708 0.0114 1.0000 0.1157
-2.500 -0.3503 0.02812 0.01594 0.0115 1.0000 0.1175
-2.250 -0.3227 0.02738 0.01504 0.0120 1.0000 0.1241
-2.000 -0.2992 0.02661 0.01422 0.0129 1.0000 0.1325
-1.750 -0.1121 0.02340 0.01403 -0.0137 1.0000 1.0000
-1.500 -0.1014 0.02346 0.01379 -0.0109 1.0000 1.0000
-1.250 -0.0902 0.02356 0.01362 -0.0083 1.0000 1.0000
-1.000 -0.0784 0.02369 0.01350 -0.0059 1.0000 1.0000
-0.750 -0.0663 0.02385 0.01342 -0.0035 1.0000 1.0000
-0.500 -0.0537 0.02404 0.01340 -0.0014 1.0000 1.0000
-0.250 -0.0408 0.02425 0.01343 0.0007 1.0000 1.0000
0.000 -0.0276 0.02449 0.01350 0.0027 1.0000 1.0000
0.250 -0.0141 0.02476 0.01363 0.0046 1.0000 1.0000
0.500 -0.0003 0.02507 0.01379 0.0064 1.0000 1.0000
0.750 0.0137 0.02540 0.01401 0.0081 1.0000 1.0000
1.000 0.0278 0.02576 0.01428 0.0097 1.0000 1.0000
1.250 0.0419 0.02616 0.01460 0.0112 1.0000 1.0000
1.500 0.0562 0.02659 0.01496 0.0127 1.0000 1.0000
1.750 0.0704 0.02706 0.01538 0.0141 1.0000 1.0000
2.000 0.0847 0.02758 0.01586 0.0154 1.0000 1.0000
2.250 0.0990 0.02813 0.01640 0.0166 1.0000 1.0000
2.500 0.1131 0.02874 0.01700 0.0178 1.0000 1.0000
2.750 0.1272 0.02940 0.01767 0.0188 1.0000 1.0000
3.000 0.1411 0.03012 0.01841 0.0198 1.0000 1.0000
3.250 0.1548 0.03091 0.01922 0.0206 1.0000 1.0000
3.500 0.1683 0.03176 0.02012 0.0214 1.0000 1.0000
3.750 0.1984 0.03307 0.02153 0.0187 0.9941 1.0000
4.000 0.2732 0.03503 0.02372 0.0074 0.9629 1.0000
4.250 0.3434 0.03639 0.02534 -0.0018 0.9305 1.0000
4.500 0.4106 0.03716 0.02644 -0.0096 0.8992 1.0000
4.750 0.4713 0.03730 0.02691 -0.0153 0.8666 1.0000
5.000 0.5431 0.03636 0.02646 -0.0212 0.8286 1.0000
5.250 0.6505 0.03237 0.02325 -0.0289 0.7787 1.0000
5.500 0.7495 0.02627 0.01794 -0.0317 0.7084 1.0000
5.750 0.7877 0.02384 0.01440 -0.0250 0.4666 1.0000
6.000 0.7893 0.02619 0.01538 -0.0196 0.3384 1.0000
6.250 0.8090 0.02851 0.01699 -0.0180 0.2632 1.0000
6.500 0.8394 0.03066 0.01883 -0.0183 0.2169 1.0000
6.750 0.8780 0.03308 0.02106 -0.0198 0.1920 1.0000
7.000 0.9064 0.03523 0.02331 -0.0196 0.1771 1.0000
7.250 0.9289 0.03715 0.02542 -0.0186 0.1654 1.0000
7.500 0.9498 0.03960 0.02828 -0.0172 0.1592 1.0000
7.750 0.9688 0.04218 0.03124 -0.0155 0.1549 1.0000
8.000 0.9875 0.04498 0.03435 -0.0140 0.1518 1.0000
8.250 1.0038 0.04827 0.03784 -0.0124 0.1491 1.0000
8.500 1.0061 0.05111 0.04127 -0.0085 0.1471 1.0000
8.750 1.0056 0.05418 0.04484 -0.0045 0.1451 1.0000
9.000 1.0033 0.05764 0.04873 -0.0007 0.1447 1.0000
9.250 0.9984 0.06145 0.05290 0.0030 0.1456 1.0000
9.500 0.9920 0.06545 0.05719 0.0066 0.1470 1.0000
9.750 0.9886 0.06977 0.06172 0.0094 0.1485 1.0000
10.000 0.9488 0.07369 0.06604 0.0153 0.1526 1.0000
10.250 0.9032 0.07813 0.07064 0.0203 0.1566 1.0000
10.500 0.8733 0.08293 0.07549 0.0228 0.1600 1.0000
10.750 0.8596 0.08842 0.08104 0.0233 0.1649 1.0000
11.000 0.7717 0.10186 0.09431 0.0151 0.1810 1.0000
11.250 0.6759 0.13167 0.12374 -0.0129 0.3545 1.0000
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Polar data table (+)
Polar graphs
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