NACA 0012-64 (naca001264-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 0012-64 (naca001264-il) Reynolds number: 50,000 Max Cl/Cd: 25.81 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001264-il-50000-n5.txt Download as CSV file: xf-naca001264-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0012-64
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.6817 0.09713 0.08914 -0.0318 1.0000 0.0743
-11.500 -0.7196 0.08625 0.07823 -0.0389 1.0000 0.0730
-11.250 -0.7633 0.07771 0.06957 -0.0428 1.0000 0.0716
-11.000 -0.7983 0.07207 0.06375 -0.0427 1.0000 0.0711
-10.750 -0.8228 0.06820 0.05971 -0.0405 1.0000 0.0712
-10.500 -0.8407 0.06508 0.05642 -0.0374 1.0000 0.0718
-10.250 -0.8525 0.06203 0.05317 -0.0345 1.0000 0.0727
-10.000 -0.8614 0.05904 0.04992 -0.0314 1.0000 0.0737
-9.750 -0.8676 0.05605 0.04664 -0.0283 1.0000 0.0747
-9.500 -0.8706 0.05310 0.04335 -0.0251 1.0000 0.0757
-9.250 -0.8700 0.05024 0.04012 -0.0221 1.0000 0.0765
-9.000 -0.8660 0.04755 0.03704 -0.0192 1.0000 0.0776
-8.750 -0.8596 0.04511 0.03414 -0.0163 1.0000 0.0792
-8.500 -0.8479 0.04300 0.03182 -0.0143 1.0000 0.0814
-8.250 -0.8328 0.04135 0.03011 -0.0127 1.0000 0.0839
-8.000 -0.8170 0.03963 0.02817 -0.0110 1.0000 0.0865
-7.750 -0.7989 0.03782 0.02610 -0.0095 1.0000 0.0889
-7.500 -0.7786 0.03611 0.02409 -0.0082 1.0000 0.0916
-7.250 -0.7568 0.03458 0.02242 -0.0072 1.0000 0.0951
-7.000 -0.7369 0.03340 0.02124 -0.0060 1.0000 0.0999
-6.750 -0.7146 0.03223 0.01989 -0.0050 1.0000 0.1057
-6.500 -0.6916 0.03103 0.01870 -0.0041 1.0000 0.1112
-6.250 -0.6698 0.02999 0.01761 -0.0030 1.0000 0.1183
-6.000 -0.6504 0.02903 0.01665 -0.0016 1.0000 0.1277
-5.750 -0.6320 0.02812 0.01574 0.0000 1.0000 0.1402
-5.500 -0.6156 0.02721 0.01489 0.0019 1.0000 0.1556
-5.250 -0.6007 0.02629 0.01408 0.0039 1.0000 0.1765
-5.000 -0.5872 0.02531 0.01328 0.0061 1.0000 0.2063
-4.750 -0.5754 0.02422 0.01252 0.0086 1.0000 0.2507
-4.500 -0.5665 0.02296 0.01182 0.0115 1.0000 0.3240
-4.250 -0.5599 0.02169 0.01144 0.0153 1.0000 0.4520
-4.000 -0.5428 0.02125 0.01178 0.0188 1.0000 0.6028
-3.750 -0.5176 0.02153 0.01225 0.0211 1.0000 0.6967
-3.500 -0.4947 0.02192 0.01260 0.0234 1.0000 0.7554
-3.250 -0.4680 0.02250 0.01309 0.0253 1.0000 0.8028
-3.000 -0.4307 0.02333 0.01376 0.0253 1.0000 0.8409
-2.750 -0.3927 0.02395 0.01419 0.0246 1.0000 0.8696
-2.500 -0.3469 0.02458 0.01460 0.0222 1.0000 0.8969
-2.250 -0.2744 0.02520 0.01498 0.0145 1.0000 0.9198
-2.000 -0.2279 0.02525 0.01487 0.0106 1.0000 0.9361
-1.750 -0.1909 0.02515 0.01465 0.0081 1.0000 0.9488
-1.500 -0.1549 0.02502 0.01442 0.0056 1.0000 0.9608
-1.250 -0.1182 0.02489 0.01420 0.0029 1.0000 0.9721
-1.000 -0.0792 0.02472 0.01397 -0.0004 1.0000 0.9818
-0.750 -0.0407 0.02456 0.01377 -0.0037 1.0000 0.9913
-0.500 -0.0041 0.02442 0.01361 -0.0068 1.0000 1.0000
-0.250 -0.0020 0.02438 0.01356 -0.0034 1.0000 1.0000
0.000 0.0000 0.02436 0.01355 0.0000 1.0000 1.0000
0.250 0.0020 0.02438 0.01356 0.0034 1.0000 1.0000
0.500 0.0041 0.02442 0.01361 0.0068 1.0000 1.0000
0.750 0.0407 0.02456 0.01377 0.0037 0.9914 1.0000
1.000 0.0791 0.02472 0.01397 0.0004 0.9818 1.0000
1.250 0.1182 0.02489 0.01420 -0.0029 0.9721 1.0000
1.500 0.1548 0.02502 0.01441 -0.0056 0.9608 1.0000
1.750 0.1908 0.02514 0.01464 -0.0081 0.9488 1.0000
2.000 0.2279 0.02525 0.01486 -0.0106 0.9361 1.0000
2.250 0.2743 0.02519 0.01497 -0.0145 0.9198 1.0000
2.500 0.3470 0.02457 0.01460 -0.0222 0.8970 1.0000
2.750 0.3926 0.02394 0.01418 -0.0246 0.8696 1.0000
3.000 0.4306 0.02332 0.01375 -0.0253 0.8410 1.0000
3.250 0.4680 0.02249 0.01308 -0.0253 0.8029 1.0000
3.500 0.4946 0.02191 0.01260 -0.0234 0.7555 1.0000
3.750 0.5175 0.02153 0.01225 -0.0210 0.6968 1.0000
4.000 0.5427 0.02125 0.01178 -0.0187 0.6030 1.0000
4.250 0.5598 0.02169 0.01143 -0.0153 0.4522 1.0000
4.500 0.5664 0.02296 0.01181 -0.0114 0.3242 1.0000
4.750 0.5753 0.02422 0.01251 -0.0085 0.2507 1.0000
5.000 0.5871 0.02531 0.01328 -0.0061 0.2064 1.0000
5.250 0.6007 0.02629 0.01408 -0.0039 0.1766 1.0000
5.500 0.6156 0.02721 0.01488 -0.0019 0.1557 1.0000
5.750 0.6320 0.02812 0.01573 0.0000 0.1403 1.0000
6.000 0.6503 0.02903 0.01664 0.0016 0.1278 1.0000
6.250 0.6698 0.02999 0.01761 0.0030 0.1183 1.0000
6.500 0.6915 0.03102 0.01869 0.0041 0.1112 1.0000
6.750 0.7146 0.03222 0.01988 0.0050 0.1058 1.0000
7.000 0.7368 0.03340 0.02124 0.0060 0.0999 1.0000
7.250 0.7568 0.03458 0.02242 0.0072 0.0951 1.0000
7.500 0.7785 0.03611 0.02408 0.0082 0.0916 1.0000
7.750 0.7989 0.03782 0.02609 0.0095 0.0889 1.0000
8.000 0.8170 0.03962 0.02816 0.0110 0.0865 1.0000
8.250 0.8328 0.04135 0.03011 0.0127 0.0839 1.0000
8.500 0.8479 0.04300 0.03182 0.0143 0.0814 1.0000
8.750 0.8596 0.04510 0.03413 0.0163 0.0792 1.0000
9.000 0.8660 0.04755 0.03703 0.0192 0.0776 1.0000
9.250 0.8701 0.05024 0.04012 0.0221 0.0765 1.0000
9.500 0.8707 0.05310 0.04335 0.0251 0.0757 1.0000
9.750 0.8677 0.05605 0.04664 0.0283 0.0747 1.0000
10.000 0.8616 0.05904 0.04993 0.0314 0.0737 1.0000
10.250 0.8528 0.06204 0.05318 0.0344 0.0727 1.0000
10.500 0.8411 0.06509 0.05643 0.0373 0.0718 1.0000
10.750 0.8235 0.06820 0.05971 0.0404 0.0712 1.0000
11.000 0.7992 0.07206 0.06374 0.0426 0.0711 1.0000
11.250 0.7641 0.07771 0.06957 0.0427 0.0716 1.0000
11.500 0.7204 0.08628 0.07827 0.0388 0.0729 1.0000
11.750 0.6825 0.09720 0.08921 0.0316 0.0742 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 0012-64 (naca001264-il)