NACA 64(1)-212 (n64212-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(1)-212 (n64212-il) Reynolds number: 100,000 Max Cl/Cd: 48.17 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64212-il-100000.txt Download as CSV file: xf-n64212-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-212
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5628 0.11061 0.10561 -0.0249 1.0000 0.1327
-10.500 -0.5180 0.10770 0.10258 -0.0182 1.0000 0.1391
-10.250 -0.5474 0.10315 0.09818 -0.0249 1.0000 0.1468
-10.000 -0.5273 0.09923 0.09422 -0.0226 1.0000 0.1508
-9.750 -0.5211 0.09603 0.09104 -0.0229 1.0000 0.1581
-9.500 -0.5382 0.09090 0.08602 -0.0268 1.0000 0.1647
-9.250 -0.5231 0.08824 0.08334 -0.0254 1.0000 0.1715
-9.000 -0.5415 0.08316 0.07838 -0.0290 1.0000 0.1801
-7.250 -0.6611 0.04004 0.03267 -0.0340 1.0000 0.0751
-7.000 -0.6529 0.03711 0.02953 -0.0316 1.0000 0.0739
-6.750 -0.6439 0.03502 0.02709 -0.0291 1.0000 0.0744
-6.500 -0.6326 0.03309 0.02483 -0.0268 1.0000 0.0749
-6.250 -0.6189 0.03112 0.02254 -0.0248 1.0000 0.0750
-6.000 -0.6033 0.02929 0.02042 -0.0230 1.0000 0.0753
-5.750 -0.5864 0.02779 0.01865 -0.0213 1.0000 0.0759
-5.500 -0.5684 0.02578 0.01657 -0.0200 1.0000 0.0782
-5.250 -0.5510 0.02462 0.01543 -0.0188 1.0000 0.0824
-5.000 -0.5323 0.02363 0.01436 -0.0175 1.0000 0.0862
-4.750 -0.5132 0.02279 0.01336 -0.0161 1.0000 0.0897
-4.500 -0.4841 0.02147 0.01225 -0.0171 0.9966 0.0982
-4.250 -0.4463 0.02034 0.01124 -0.0195 0.9899 0.1114
-4.000 -0.4071 0.01916 0.01024 -0.0226 0.9834 0.1408
-3.750 -0.3874 0.01616 0.00972 -0.0224 0.9755 0.5703
-3.500 -0.3548 0.01694 0.01056 -0.0220 0.9669 0.6590
-3.250 -0.3222 0.01766 0.01125 -0.0216 0.9584 0.6979
-3.000 -0.2953 0.01836 0.01192 -0.0200 0.9491 0.7293
-2.750 -0.2669 0.01944 0.01302 -0.0174 0.9421 0.7670
-2.500 -0.2500 0.02018 0.01376 -0.0132 0.9320 0.7953
-2.250 -0.2132 0.02062 0.01409 -0.0134 0.9268 0.8131
-2.000 -0.1896 0.02060 0.01398 -0.0128 0.9168 0.8239
-1.750 -0.1452 0.02061 0.01386 -0.0158 0.9123 0.8322
-1.500 -0.1222 0.02054 0.01369 -0.0154 0.9022 0.8428
-1.250 -0.0792 0.02051 0.01357 -0.0181 0.8976 0.8508
-1.000 -0.0577 0.02049 0.01349 -0.0175 0.8881 0.8602
-0.750 -0.0183 0.02040 0.01332 -0.0198 0.8829 0.8688
-0.500 0.0051 0.02041 0.01330 -0.0193 0.8738 0.8776
-0.250 0.0406 0.02031 0.01315 -0.0210 0.8681 0.8869
0.000 0.0669 0.02040 0.01322 -0.0211 0.8603 0.8961
0.250 0.1017 0.02036 0.01315 -0.0226 0.8542 0.9052
0.500 0.1302 0.02038 0.01316 -0.0232 0.8472 0.9160
0.750 0.1689 0.02044 0.01323 -0.0256 0.8406 0.9241
1.000 0.2131 0.02036 0.01316 -0.0287 0.8366 0.9327
1.250 0.2424 0.02058 0.01342 -0.0300 0.8280 0.9444
1.500 0.2960 0.02051 0.01340 -0.0351 0.8234 0.9499
1.750 0.3403 0.02053 0.01347 -0.0387 0.8180 0.9589
2.000 0.3909 0.02060 0.01363 -0.0438 0.8105 0.9658
2.250 0.4411 0.02036 0.01347 -0.0480 0.8057 0.9730
2.500 0.4842 0.02055 0.01379 -0.0520 0.7964 0.9826
2.750 0.5355 0.02028 0.01363 -0.0565 0.7909 0.9899
3.000 0.5794 0.02038 0.01389 -0.0607 0.7810 1.0000
3.250 0.5946 0.02037 0.01395 -0.0586 0.7720 1.0000
3.500 0.6088 0.02021 0.01385 -0.0560 0.7604 1.0000
3.750 0.6223 0.01981 0.01349 -0.0526 0.7454 1.0000
4.000 0.6393 0.01900 0.01269 -0.0491 0.7279 1.0000
4.250 0.6504 0.01838 0.01212 -0.0449 0.7061 1.0000
4.500 0.6722 0.01724 0.01090 -0.0414 0.6830 1.0000
4.750 0.6861 0.01683 0.01054 -0.0381 0.6591 1.0000
5.000 0.7065 0.01632 0.01005 -0.0357 0.6335 1.0000
5.250 0.7266 0.01585 0.00963 -0.0332 0.5980 1.0000
5.500 0.7442 0.01545 0.00914 -0.0302 0.5328 1.0000
5.750 0.7349 0.01734 0.00927 -0.0239 0.2366 1.0000
6.000 0.7342 0.02003 0.01097 -0.0204 0.1364 1.0000
6.250 0.7479 0.02149 0.01224 -0.0185 0.1122 1.0000
6.500 0.7650 0.02289 0.01352 -0.0170 0.0991 1.0000
6.750 0.7858 0.02440 0.01491 -0.0160 0.0895 1.0000
7.000 0.8103 0.02590 0.01629 -0.0156 0.0818 1.0000
7.250 0.8400 0.02790 0.01831 -0.0157 0.0771 1.0000
7.500 0.8670 0.02948 0.02001 -0.0155 0.0721 1.0000
7.750 0.8952 0.03172 0.02221 -0.0158 0.0682 1.0000
8.000 0.9236 0.03486 0.02553 -0.0159 0.0666 1.0000
8.250 0.9466 0.03736 0.02840 -0.0151 0.0661 1.0000
8.500 0.9666 0.04010 0.03154 -0.0140 0.0657 1.0000
8.750 0.9827 0.04279 0.03467 -0.0126 0.0648 1.0000
9.000 0.9958 0.04587 0.03819 -0.0111 0.0643 1.0000
9.250 1.0072 0.04978 0.04245 -0.0097 0.0652 1.0000
9.500 1.0209 0.05552 0.04834 -0.0093 0.0668 1.0000
9.750 1.0009 0.05936 0.05330 -0.0043 0.0752 1.0000
10.000 0.9329 0.05590 0.05046 0.0015 0.0776 1.0000
10.250 0.8862 0.06095 0.05601 0.0056 0.0851 1.0000
10.500 0.8485 0.06640 0.06165 0.0064 0.0874 1.0000
10.750 0.8077 0.07442 0.06991 0.0049 0.0969 1.0000
11.000 0.7634 0.08242 0.07802 0.0013 0.0970 1.0000
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Polar data table (+)
Polar graphs
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