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NACA 66(1)-212 (naca661212-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 66(1)-212 (naca661212-il)
Reynolds number: 200,000
Max Cl/Cd: 46.79 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca661212-il-200000-n5.txt
Download as CSV file: xf-naca661212-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66(1)-212                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5184   0.09064   0.08698  -0.0510   1.0000   0.0188
 -11.000  -0.5888   0.06776   0.06399  -0.0663   1.0000   0.0171
 -10.750  -0.6174   0.06187   0.05796  -0.0675   1.0000   0.0169
 -10.500  -0.6394   0.05851   0.05451  -0.0661   1.0000   0.0170
 -10.250  -0.6595   0.05542   0.05131  -0.0642   0.9932   0.0170
 -10.000  -0.6595   0.05208   0.04779  -0.0657   0.9803   0.0173
  -9.750  -0.6478   0.05026   0.04586  -0.0669   0.9718   0.0177
  -9.500  -0.6355   0.04816   0.04360  -0.0680   0.9646   0.0185
  -9.250  -0.6326   0.04424   0.03934  -0.0675   0.9555   0.0188
  -9.000  -0.6265   0.04041   0.03508  -0.0668   0.9479   0.0191
  -8.750  -0.6189   0.03716   0.03143  -0.0653   0.9398   0.0194
  -8.500  -0.6073   0.03421   0.02807  -0.0639   0.9334   0.0199
  -8.250  -0.5945   0.03175   0.02521  -0.0623   0.9267   0.0204
  -8.000  -0.5767   0.02981   0.02282  -0.0611   0.9220   0.0216
  -7.750  -0.5590   0.02844   0.02106  -0.0597   0.9163   0.0223
  -7.500  -0.5393   0.02612   0.01848  -0.0589   0.9117   0.0228
  -7.250  -0.5164   0.02451   0.01669  -0.0585   0.9080   0.0234
  -7.000  -0.4931   0.02332   0.01536  -0.0581   0.9042   0.0240
  -6.750  -0.4700   0.02230   0.01422  -0.0576   0.8996   0.0248
  -6.500  -0.4460   0.02149   0.01329  -0.0572   0.8957   0.0261
  -6.250  -0.4211   0.02068   0.01235  -0.0568   0.8927   0.0276
  -6.000  -0.3963   0.01981   0.01137  -0.0565   0.8896   0.0286
  -5.750  -0.3725   0.01904   0.01052  -0.0559   0.8857   0.0294
  -5.500  -0.3488   0.01840   0.00979  -0.0553   0.8822   0.0301
  -5.250  -0.3283   0.01733   0.00870  -0.0544   0.8791   0.0317
  -5.000  -0.3066   0.01670   0.00805  -0.0535   0.8764   0.0335
  -4.750  -0.2855   0.01627   0.00761  -0.0526   0.8722   0.0362
  -4.500  -0.2637   0.01585   0.00713  -0.0518   0.8685   0.0385
  -4.250  -0.2410   0.01546   0.00664  -0.0511   0.8655   0.0404
  -4.000  -0.2189   0.01497   0.00612  -0.0502   0.8630   0.0444
  -3.750  -0.1955   0.01465   0.00576  -0.0497   0.8605   0.0499
  -3.500  -0.1731   0.01435   0.00547  -0.0490   0.8570   0.0576
  -3.250  -0.1513   0.01393   0.00517  -0.0482   0.8539   0.0853
  -3.000  -0.1392   0.01262   0.00474  -0.0462   0.8505   0.2907
  -2.750  -0.1343   0.01106   0.00458  -0.0424   0.8475   0.5958
  -2.500  -0.1138   0.01122   0.00509  -0.0402   0.8449   0.7211
  -2.250  -0.0916   0.01157   0.00548  -0.0386   0.8418   0.7618
  -2.000  -0.0677   0.01191   0.00582  -0.0372   0.8392   0.7833
  -1.750  -0.0427   0.01214   0.00602  -0.0362   0.8370   0.7965
  -1.500  -0.0174   0.01233   0.00617  -0.0354   0.8350   0.8080
  -1.250   0.0088   0.01246   0.00625  -0.0348   0.8331   0.8166
  -1.000   0.0361   0.01246   0.00619  -0.0348   0.8313   0.8212
  -0.750   0.0607   0.01256   0.00629  -0.0344   0.8282   0.8243
  -0.500   0.0865   0.01261   0.00632  -0.0342   0.8256   0.8273
  -0.250   0.1131   0.01262   0.00630  -0.0343   0.8232   0.8301
   0.000   0.1403   0.01260   0.00625  -0.0345   0.8209   0.8332
   0.250   0.1682   0.01258   0.00622  -0.0347   0.8190   0.8357
   0.500   0.1964   0.01259   0.00622  -0.0350   0.8175   0.8373
   0.750   0.2215   0.01266   0.00632  -0.0347   0.8141   0.8394
   1.000   0.2464   0.01271   0.00641  -0.0344   0.8100   0.8420
   1.250   0.2736   0.01270   0.00642  -0.0344   0.8066   0.8448
   1.500   0.3023   0.01265   0.00638  -0.0347   0.8039   0.8476
   1.750   0.3302   0.01262   0.00638  -0.0350   0.8008   0.8501
   2.000   0.3537   0.01270   0.00655  -0.0343   0.7955   0.8522
   2.250   0.3813   0.01264   0.00655  -0.0342   0.7910   0.8542
   2.500   0.4084   0.01246   0.00641  -0.0339   0.7830   0.8567
   2.750   0.4381   0.01210   0.00608  -0.0337   0.7722   0.8593
   3.000   0.4637   0.01183   0.00584  -0.0329   0.7572   0.8625
   3.250   0.4866   0.01160   0.00565  -0.0316   0.7354   0.8655
   3.500   0.5088   0.01128   0.00530  -0.0299   0.6942   0.8679
   3.750   0.5264   0.01125   0.00476  -0.0270   0.5625   0.8709
   4.000   0.5266   0.01237   0.00503  -0.0219   0.4032   0.8760
   4.250   0.5283   0.01357   0.00555  -0.0177   0.2597   0.8811
   4.500   0.5315   0.01480   0.00613  -0.0138   0.1225   0.8861
   4.750   0.5438   0.01564   0.00663  -0.0115   0.0620   0.8914
   5.000   0.5620   0.01610   0.00708  -0.0100   0.0504   0.8958
   5.250   0.5799   0.01652   0.00754  -0.0084   0.0445   0.9001
   5.500   0.5983   0.01695   0.00802  -0.0069   0.0401   0.9053
   5.750   0.6135   0.01752   0.00863  -0.0050   0.0368   0.9109
   6.000   0.6290   0.01798   0.00917  -0.0029   0.0345   0.9168
   6.500   0.6621   0.01903   0.01038   0.0005   0.0303   0.9309
   6.750   0.6787   0.01972   0.01111   0.0020   0.0287   0.9391
   7.000   0.6962   0.02066   0.01209   0.0033   0.0274   0.9471
   7.250   0.7186   0.02183   0.01331   0.0037   0.0263   0.9544
   7.500   0.7460   0.02273   0.01433   0.0032   0.0254   0.9616
   7.750   0.7758   0.02369   0.01540   0.0023   0.0241   0.9688
   8.000   0.8066   0.02471   0.01652   0.0010   0.0226   0.9774
   8.250   0.8385   0.02596   0.01790  -0.0005   0.0217   0.9900
   8.500   0.8652   0.02723   0.01926  -0.0010   0.0210   1.0000
   8.750   0.8907   0.02868   0.02082  -0.0014   0.0204   1.0000
   9.000   0.9164   0.03064   0.02290  -0.0018   0.0199   1.0000
   9.250   0.9393   0.03313   0.02563  -0.0018   0.0195   1.0000
   9.500   0.9562   0.03503   0.02786  -0.0007   0.0193   1.0000
   9.750   0.9687   0.03695   0.03015   0.0010   0.0187   1.0000
  10.000   0.9783   0.03905   0.03259   0.0030   0.0180   1.0000
  10.250   0.9833   0.04147   0.03533   0.0054   0.0176   1.0000
  10.500   0.9834   0.04407   0.03824   0.0084   0.0173   1.0000
  10.750   0.9789   0.04689   0.04136   0.0115   0.0171   1.0000
  11.000   0.9709   0.04981   0.04456   0.0146   0.0169   1.0000
  11.250   0.9597   0.05301   0.04802   0.0174   0.0168   1.0000
  11.500   0.9453   0.05646   0.05172   0.0199   0.0167   1.0000
  11.750   0.9276   0.06037   0.05587   0.0218   0.0168   1.0000
  12.000   0.9075   0.06473   0.06044   0.0229   0.0167   1.0000
  12.250   0.8843   0.06980   0.06572   0.0230   0.0168   1.0000
  12.500   0.8597   0.07557   0.07169   0.0217   0.0169   1.0000
  12.750   0.8312   0.08285   0.07914   0.0186   0.0170   1.0000
  13.000   0.7995   0.09259   0.08903   0.0127   0.0172   1.0000
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