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NACA 65(1)-412 (naca651412-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 65(1)-412 (naca651412-il)
Reynolds number: 1,000,000
Max Cl/Cd: 116.34 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca651412-il-1000000.txt
Download as CSV file: xf-naca651412-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(1)-412                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5193   0.05973   0.05809  -0.0709   0.9980   0.0131
  -9.500  -0.6236   0.02484   0.02128  -0.0851   0.9601   0.0116
  -9.250  -0.6017   0.02320   0.01935  -0.0854   0.9500   0.0119
  -9.000  -0.5931   0.01912   0.01474  -0.0841   0.9370   0.0124
  -8.750  -0.5710   0.01840   0.01392  -0.0837   0.9274   0.0128
  -8.500  -0.5479   0.01805   0.01350  -0.0833   0.9182   0.0132
  -8.250  -0.5251   0.01739   0.01271  -0.0828   0.9099   0.0136
  -8.000  -0.5019   0.01675   0.01196  -0.0823   0.9013   0.0141
  -7.750  -0.4780   0.01617   0.01126  -0.0819   0.8938   0.0147
  -7.500  -0.4535   0.01568   0.01064  -0.0816   0.8857   0.0153
  -7.250  -0.4286   0.01527   0.01011  -0.0812   0.8785   0.0156
  -7.000  -0.4075   0.01354   0.00819  -0.0805   0.8706   0.0162
  -6.750  -0.3834   0.01287   0.00747  -0.0801   0.8637   0.0169
  -6.500  -0.3580   0.01250   0.00707  -0.0799   0.8565   0.0176
  -6.250  -0.3324   0.01214   0.00664  -0.0797   0.8499   0.0183
  -6.000  -0.3066   0.01179   0.00624  -0.0796   0.8428   0.0190
  -5.750  -0.2806   0.01150   0.00587  -0.0794   0.8362   0.0198
  -5.500  -0.2543   0.01116   0.00549  -0.0793   0.8294   0.0203
  -5.250  -0.2306   0.01038   0.00461  -0.0788   0.8229   0.0211
  -5.000  -0.2051   0.00986   0.00405  -0.0787   0.8167   0.0222
  -4.750  -0.1785   0.00960   0.00376  -0.0786   0.8103   0.0233
  -4.500  -0.1515   0.00938   0.00350  -0.0787   0.8044   0.0246
  -4.250  -0.1243   0.00915   0.00323  -0.0787   0.7980   0.0257
  -4.000  -0.0970   0.00899   0.00300  -0.0787   0.7922   0.0265
  -3.750  -0.0701   0.00854   0.00251  -0.0788   0.7865   0.0289
  -3.500  -0.0426   0.00835   0.00229  -0.0789   0.7807   0.0314
  -3.250  -0.0148   0.00822   0.00211  -0.0790   0.7754   0.0339
  -3.000   0.0131   0.00800   0.00188  -0.0791   0.7695   0.0396
  -2.750   0.0408   0.00781   0.00171  -0.0793   0.7640   0.0528
  -2.500   0.0671   0.00701   0.00145  -0.0797   0.7589   0.2131
  -2.250   0.0928   0.00579   0.00117  -0.0805   0.7534   0.4951
  -2.000   0.1206   0.00558   0.00115  -0.0807   0.7482   0.5755
  -1.750   0.1492   0.00552   0.00113  -0.0810   0.7432   0.6039
  -1.500   0.1777   0.00547   0.00114  -0.0812   0.7380   0.6315
  -1.250   0.2059   0.00548   0.00116  -0.0813   0.7331   0.6550
  -1.000   0.2345   0.00548   0.00120  -0.0815   0.7283   0.6774
  -0.750   0.2630   0.00550   0.00123  -0.0816   0.7233   0.6919
  -0.500   0.2913   0.00553   0.00124  -0.0818   0.7186   0.7003
  -0.250   0.3201   0.00554   0.00125  -0.0820   0.7141   0.7057
   0.000   0.3490   0.00556   0.00126  -0.0823   0.7093   0.7105
   0.250   0.3773   0.00558   0.00127  -0.0825   0.7048   0.7154
   0.500   0.4060   0.00561   0.00130  -0.0828   0.7004   0.7205
   0.750   0.4349   0.00563   0.00133  -0.0831   0.6959   0.7256
   1.000   0.4632   0.00565   0.00136  -0.0832   0.6914   0.7306
   1.250   0.4917   0.00570   0.00140  -0.0835   0.6866   0.7361
   1.500   0.5202   0.00571   0.00144  -0.0837   0.6802   0.7414
   1.750   0.5481   0.00576   0.00148  -0.0837   0.6731   0.7467
   2.000   0.5762   0.00577   0.00152  -0.0839   0.6634   0.7524
   2.250   0.6040   0.00581   0.00156  -0.0839   0.6523   0.7579
   2.500   0.6314   0.00586   0.00161  -0.0839   0.6394   0.7638
   2.750   0.6586   0.00594   0.00165  -0.0838   0.6209   0.7698
   3.000   0.6853   0.00603   0.00172  -0.0837   0.6029   0.7755
   3.250   0.7120   0.00615   0.00182  -0.0835   0.5812   0.7820
   3.500   0.7376   0.00634   0.00192  -0.0832   0.5487   0.7882
   3.750   0.7602   0.00676   0.00211  -0.0823   0.4850   0.7949
   4.000   0.7755   0.00784   0.00259  -0.0804   0.3526   0.8019
   4.250   0.7902   0.00897   0.00317  -0.0785   0.2251   0.8091
   4.500   0.8055   0.01006   0.00374  -0.0767   0.1117   0.8168
   4.750   0.8234   0.01088   0.00424  -0.0752   0.0457   0.8246
   5.000   0.8467   0.01126   0.00458  -0.0745   0.0333   0.8324
   5.250   0.8703   0.01157   0.00492  -0.0739   0.0289   0.8403
   5.500   0.8934   0.01194   0.00533  -0.0731   0.0253   0.8483
   5.750   0.9170   0.01222   0.00566  -0.0725   0.0232   0.8569
   6.000   0.9387   0.01262   0.00609  -0.0715   0.0210   0.8659
   6.250   0.9590   0.01314   0.00669  -0.0703   0.0195   0.8759
   6.500   0.9813   0.01341   0.00702  -0.0694   0.0186   0.8861
   6.750   1.0022   0.01375   0.00741  -0.0683   0.0176   0.8967
   7.000   1.0222   0.01411   0.00782  -0.0670   0.0168   0.9084
   7.250   1.0398   0.01457   0.00834  -0.0653   0.0161   0.9220
   7.500   1.0508   0.01525   0.00912  -0.0623   0.0153   0.9405
   7.750   1.0623   0.01592   0.00992  -0.0595   0.0149   1.0000
   8.000   1.0809   0.01645   0.01050  -0.0582   0.0146   1.0000
   8.250   1.0987   0.01701   0.01109  -0.0568   0.0143   1.0000
   8.500   1.1147   0.01767   0.01181  -0.0551   0.0140   1.0000
   8.750   1.1301   0.01839   0.01257  -0.0534   0.0137   1.0000
   9.000   1.1465   0.01905   0.01327  -0.0519   0.0133   1.0000
   9.250   1.1629   0.01970   0.01396  -0.0505   0.0129   1.0000
   9.500   1.1792   0.02035   0.01465  -0.0492   0.0126   1.0000
   9.750   1.1941   0.02114   0.01548  -0.0477   0.0122   1.0000
  10.000   1.2080   0.02207   0.01644  -0.0461   0.0119   1.0000
  10.250   1.2201   0.02334   0.01778  -0.0444   0.0117   1.0000
  10.500   1.2330   0.02604   0.02064  -0.0429   0.0112   1.0000
  10.750   1.2478   0.02691   0.02160  -0.0415   0.0111   1.0000
  11.000   1.2618   0.02784   0.02261  -0.0402   0.0110   1.0000
  11.250   1.2756   0.02911   0.02400  -0.0389   0.0109   1.0000
  11.500   1.2882   0.03047   0.02549  -0.0375   0.0107   1.0000
  11.750   1.2995   0.03183   0.02697  -0.0361   0.0105   1.0000
  12.000   1.3094   0.03324   0.02850  -0.0346   0.0103   1.0000
  12.250   1.3183   0.03463   0.03000  -0.0332   0.0101   1.0000
  12.500   1.3253   0.03632   0.03181  -0.0317   0.0099   1.0000
  12.750   1.3307   0.03821   0.03385  -0.0302   0.0097   1.0000
  13.000   1.3355   0.03999   0.03574  -0.0289   0.0095   1.0000
  13.250   1.3387   0.04195   0.03781  -0.0276   0.0094   1.0000
  13.500   1.3409   0.04401   0.04000  -0.0265   0.0092   1.0000
  13.750   1.3409   0.04640   0.04252  -0.0255   0.0091   1.0000
  14.000   1.3408   0.04882   0.04505  -0.0247   0.0090   1.0000
  14.250   1.3387   0.05156   0.04792  -0.0241   0.0089   1.0000
  14.500   1.3363   0.05440   0.05086  -0.0238   0.0088   1.0000
  14.750   1.3283   0.05820   0.05482  -0.0236   0.0088   1.0000
  15.000   1.3209   0.06199   0.05873  -0.0239   0.0086   1.0000
  15.250   1.3072   0.06697   0.06389  -0.0246   0.0086   1.0000
  15.500   1.2904   0.07271   0.06982  -0.0260   0.0085   1.0000
  15.750   1.2677   0.07977   0.07708  -0.0283   0.0085   1.0000
  16.000   1.2496   0.08662   0.08411  -0.0312   0.0085   1.0000
  16.250   1.2279   0.09469   0.09237  -0.0352   0.0085   1.0000
  16.500   1.2049   0.10367   0.10153  -0.0403   0.0085   1.0000
  16.750   1.1801   0.11402   0.11208  -0.0466   0.0086   1.0000
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