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NACA 64(1)-212 MOD A (n64212ma-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 64(1)-212 MOD A (n64212ma-il)
Reynolds number: 500,000
Max Cl/Cd: 68.67 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64212ma-il-500000-n5.txt
Download as CSV file: xf-n64212ma-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-212 MOD A                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4156   0.09797   0.09547  -0.0282   1.0000   0.0163
 -10.250  -0.4410   0.08738   0.08488  -0.0346   1.0000   0.0175
 -10.000  -0.4398   0.08383   0.08135  -0.0364   1.0000   0.0175
  -9.750  -0.4371   0.08074   0.07830  -0.0380   1.0000   0.0177
  -9.500  -0.4450   0.07515   0.07273  -0.0420   1.0000   0.0177
  -9.250  -0.4495   0.06702   0.06456  -0.0528   0.9631   0.0178
  -9.000  -0.4575   0.05953   0.05685  -0.0624   0.9178   0.0179
  -8.750  -0.4626   0.05654   0.05369  -0.0624   0.8909   0.0180
  -8.500  -0.4674   0.05318   0.05015  -0.0619   0.8718   0.0182
  -7.500  -0.4813   0.02891   0.02414  -0.0569   0.8219   0.0207
  -7.250  -0.4620   0.02756   0.02261  -0.0561   0.8104   0.0209
  -7.000  -0.4402   0.02659   0.02152  -0.0556   0.7993   0.0211
  -6.500  -0.3947   0.02491   0.01957  -0.0546   0.7746   0.0216
  -6.250  -0.3724   0.02352   0.01796  -0.0540   0.7626   0.0220
  -6.000  -0.3507   0.02106   0.01515  -0.0532   0.7509   0.0227
  -5.750  -0.3281   0.01868   0.01236  -0.0524   0.7397   0.0233
  -5.500  -0.3035   0.01714   0.01052  -0.0518   0.7271   0.0237
  -5.250  -0.2780   0.01619   0.00931  -0.0513   0.7136   0.0241
  -5.000  -0.2526   0.01548   0.00850  -0.0508   0.6979   0.0244
  -4.750  -0.2265   0.01502   0.00797  -0.0505   0.6804   0.0247
  -4.500  -0.2003   0.01470   0.00755  -0.0501   0.6609   0.0250
  -4.250  -0.1742   0.01437   0.00710  -0.0497   0.6390   0.0255
  -4.000  -0.1482   0.01403   0.00662  -0.0493   0.6135   0.0260
  -3.750  -0.1226   0.01367   0.00609  -0.0488   0.5818   0.0265
  -3.500  -0.0974   0.01339   0.00559  -0.0482   0.5394   0.0269
  -3.250  -0.0760   0.01369   0.00527  -0.0472   0.3822   0.0272
  -3.000  -0.0553   0.01431   0.00517  -0.0464   0.1833   0.0276
  -2.500  -0.0039   0.01401   0.00459  -0.0456   0.1079   0.0283
  -2.250   0.0229   0.01383   0.00439  -0.0454   0.1044   0.0288
  -2.000   0.0500   0.01367   0.00420  -0.0452   0.1026   0.0294
  -1.750   0.0771   0.01354   0.00405  -0.0450   0.1011   0.0302
  -1.500   0.1043   0.01342   0.00390  -0.0448   0.1000   0.0311
  -1.250   0.1316   0.01331   0.00375  -0.0447   0.0991   0.0318
  -1.000   0.1589   0.01316   0.00361  -0.0445   0.0984   0.0325
  -0.750   0.1864   0.01308   0.00352  -0.0444   0.0978   0.0334
  -0.500   0.2139   0.01302   0.00345  -0.0443   0.0972   0.0344
  -0.250   0.2415   0.01298   0.00340  -0.0442   0.0967   0.0356
   0.000   0.2690   0.01295   0.00336  -0.0440   0.0963   0.0370
   0.250   0.2965   0.01295   0.00336  -0.0439   0.0959   0.0392
   0.500   0.3240   0.01297   0.00338  -0.0438   0.0956   0.0422
   0.750   0.3514   0.01300   0.00341  -0.0436   0.0952   0.0463
   1.000   0.3787   0.01305   0.00346  -0.0435   0.0949   0.0532
   1.250   0.4059   0.01308   0.00352  -0.0434   0.0947   0.0685
   1.500   0.4316   0.01174   0.00351  -0.0441   0.0944   0.5594
   1.750   0.4580   0.01169   0.00369  -0.0438   0.0942   0.6349
   2.000   0.4843   0.01179   0.00388  -0.0435   0.0939   0.6752
   2.250   0.5110   0.01186   0.00404  -0.0432   0.0934   0.7080
   2.500   0.5374   0.01193   0.00420  -0.0427   0.0924   0.7411
   2.750   0.5636   0.01204   0.00437  -0.0423   0.0914   0.7654
   3.000   0.5901   0.01219   0.00453  -0.0419   0.0907   0.7792
   3.250   0.6165   0.01236   0.00470  -0.0416   0.0901   0.7874
   3.500   0.6427   0.01254   0.00488  -0.0413   0.0896   0.7963
   4.000   0.6945   0.01295   0.00528  -0.0405   0.0883   0.8135
   4.250   0.7209   0.01309   0.00544  -0.0402   0.0876   0.8224
   4.500   0.7470   0.01324   0.00562  -0.0398   0.0869   0.8308
   4.750   0.7726   0.01340   0.00580  -0.0394   0.0860   0.8407
   5.000   0.7981   0.01357   0.00599  -0.0389   0.0853   0.8504
   5.250   0.8230   0.01374   0.00619  -0.0383   0.0845   0.8610
   5.500   0.8477   0.01392   0.00639  -0.0378   0.0838   0.8713
   5.750   0.8719   0.01409   0.00659  -0.0370   0.0830   0.8833
   6.000   0.8958   0.01421   0.00677  -0.0362   0.0818   0.8962
   6.250   0.9191   0.01435   0.00697  -0.0353   0.0805   0.9107
   6.500   0.9419   0.01447   0.00713  -0.0343   0.0792   0.9275
   6.750   0.9652   0.01461   0.00732  -0.0334   0.0776   0.9496
   7.000   0.9961   0.01478   0.00754  -0.0342   0.0741   1.0000
   7.250   1.0232   0.01490   0.00747  -0.0343   0.0547   1.0000
   7.500   1.0459   0.01538   0.00792  -0.0337   0.0519   1.0000
   7.750   1.0682   0.01588   0.00843  -0.0330   0.0498   1.0000
   8.000   1.0915   0.01626   0.00884  -0.0324   0.0481   1.0000
   8.250   1.1141   0.01669   0.00928  -0.0318   0.0464   1.0000
   8.500   1.1373   0.01702   0.00965  -0.0312   0.0443   1.0000
   8.750   1.1603   0.01734   0.01000  -0.0306   0.0402   1.0000
   9.000   1.1811   0.01784   0.01047  -0.0297   0.0362   1.0000
   9.250   1.2014   0.01833   0.01094  -0.0288   0.0345   1.0000
   9.500   1.2213   0.01880   0.01142  -0.0278   0.0337   1.0000
   9.750   1.2395   0.01928   0.01191  -0.0265   0.0331   1.0000
  10.000   1.2566   0.01979   0.01244  -0.0251   0.0325   1.0000
  10.250   1.2731   0.02033   0.01301  -0.0236   0.0321   1.0000
  10.500   1.2889   0.02092   0.01363  -0.0222   0.0317   1.0000
  10.750   1.3044   0.02152   0.01428  -0.0207   0.0315   1.0000
  11.000   1.3195   0.02217   0.01497  -0.0193   0.0312   1.0000
  11.250   1.3338   0.02287   0.01572  -0.0179   0.0309   1.0000
  11.500   1.3474   0.02365   0.01654  -0.0165   0.0306   1.0000
  11.750   1.3601   0.02450   0.01745  -0.0151   0.0303   1.0000
  12.000   1.3719   0.02544   0.01845  -0.0138   0.0300   1.0000
  12.250   1.3821   0.02652   0.01958  -0.0124   0.0295   1.0000
  12.500   1.3909   0.02773   0.02085  -0.0110   0.0292   1.0000
  12.750   1.3993   0.02901   0.02220  -0.0098   0.0290   1.0000
  13.000   1.4062   0.03046   0.02370  -0.0086   0.0288   1.0000
  13.250   1.4158   0.03174   0.02506  -0.0076   0.0286   1.0000
  13.500   1.4239   0.03316   0.02657  -0.0068   0.0284   1.0000
  13.750   1.4309   0.03475   0.02824  -0.0060   0.0282   1.0000
  14.000   1.4368   0.03648   0.03005  -0.0053   0.0281   1.0000
  14.250   1.4416   0.03837   0.03203  -0.0047   0.0279   1.0000
  14.500   1.4457   0.04040   0.03415  -0.0043   0.0276   1.0000
  14.750   1.4485   0.04262   0.03646  -0.0040   0.0274   1.0000
  15.000   1.4498   0.04510   0.03903  -0.0039   0.0272   1.0000
  15.250   1.4496   0.04782   0.04184  -0.0040   0.0270   1.0000
  15.500   1.4481   0.05081   0.04492  -0.0044   0.0268   1.0000
  15.750   1.4452   0.05411   0.04833  -0.0050   0.0267   1.0000
  16.000   1.4408   0.05776   0.05208  -0.0059   0.0266   1.0000
  16.250   1.4350   0.06177   0.05620  -0.0071   0.0265   1.0000
  16.500   1.4273   0.06627   0.06080  -0.0088   0.0264   1.0000
  16.750   1.4177   0.07123   0.06587  -0.0108   0.0262   1.0000
  17.000   1.4078   0.07651   0.07126  -0.0132   0.0262   1.0000
  17.250   1.3960   0.08234   0.07720  -0.0160   0.0261   1.0000
  17.500   1.3861   0.08816   0.08317  -0.0190   0.0260   1.0000
  17.750   1.3750   0.09440   0.08955  -0.0224   0.0259   1.0000
  18.000   1.3630   0.10098   0.09626  -0.0260   0.0258   1.0000
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