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NACA 63-209 (naca63209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 63-209 (naca63209-il)
Reynolds number: 1,000,000
Max Cl/Cd: 72.66 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca63209-il-1000000-n5.txt
Download as CSV file: xf-naca63209-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-209                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.9033   0.05353   0.05185  -0.0385   1.0000   0.0037
 -12.250  -0.9821   0.04018   0.03808  -0.0448   1.0000   0.0035
 -12.000  -1.0167   0.03469   0.03224  -0.0428   1.0000   0.0035
 -11.750  -1.0164   0.03167   0.02897  -0.0419   1.0000   0.0036
 -11.500  -1.0166   0.02807   0.02500  -0.0408   1.0000   0.0036
 -11.250  -1.0046   0.02597   0.02266  -0.0401   1.0000   0.0037
 -11.000  -0.9895   0.02421   0.02069  -0.0394   1.0000   0.0038
 -10.750  -0.9725   0.02260   0.01886  -0.0389   1.0000   0.0039
 -10.500  -0.9535   0.02127   0.01735  -0.0384   1.0000   0.0039
 -10.250  -0.9350   0.01972   0.01559  -0.0378   1.0000   0.0041
 -10.000  -0.9151   0.01834   0.01401  -0.0373   1.0000   0.0043
  -9.750  -0.8925   0.01754   0.01311  -0.0370   1.0000   0.0046
  -9.500  -0.8689   0.01692   0.01242  -0.0367   1.0000   0.0048
  -9.250  -0.8452   0.01628   0.01171  -0.0364   1.0000   0.0050
  -9.000  -0.8212   0.01571   0.01106  -0.0361   1.0000   0.0052
  -8.750  -0.7973   0.01511   0.01038  -0.0357   1.0000   0.0055
  -8.500  -0.7733   0.01452   0.00971  -0.0354   1.0000   0.0058
  -8.250  -0.7490   0.01404   0.00916  -0.0350   1.0000   0.0061
  -8.000  -0.7216   0.01357   0.00860  -0.0353   0.9973   0.0064
  -7.750  -0.6907   0.01279   0.00774  -0.0365   0.9886   0.0069
  -7.500  -0.6580   0.01238   0.00729  -0.0379   0.9794   0.0074
  -7.250  -0.6252   0.01197   0.00685  -0.0393   0.9690   0.0079
  -7.000  -0.5937   0.01157   0.00639  -0.0404   0.9563   0.0085
  -6.750  -0.5652   0.01122   0.00594  -0.0407   0.9415   0.0090
  -6.500  -0.5388   0.01091   0.00555  -0.0405   0.9264   0.0094
  -6.250  -0.5126   0.01070   0.00526  -0.0403   0.9127   0.0096
  -6.000  -0.4875   0.01014   0.00459  -0.0399   0.8998   0.0107
  -5.750  -0.4612   0.00986   0.00426  -0.0397   0.8880   0.0115
  -5.500  -0.4347   0.00961   0.00394  -0.0395   0.8765   0.0121
  -5.250  -0.4080   0.00937   0.00363  -0.0394   0.8654   0.0128
  -5.000  -0.3809   0.00917   0.00337  -0.0393   0.8541   0.0136
  -4.750  -0.3537   0.00898   0.00312  -0.0392   0.8435   0.0141
  -4.500  -0.3266   0.00874   0.00279  -0.0392   0.8331   0.0146
  -4.000  -0.2718   0.00828   0.00222  -0.0391   0.8125   0.0181
  -3.750  -0.2441   0.00814   0.00204  -0.0391   0.8028   0.0203
  -3.500  -0.2164   0.00800   0.00185  -0.0391   0.7930   0.0232
  -3.250  -0.1886   0.00784   0.00168  -0.0392   0.7831   0.0283
  -3.000  -0.1607   0.00773   0.00153  -0.0392   0.7736   0.0326
  -2.750  -0.1328   0.00760   0.00139  -0.0393   0.7642   0.0417
  -2.500  -0.1050   0.00741   0.00126  -0.0394   0.7544   0.0656
  -2.250  -0.0772   0.00714   0.00112  -0.0395   0.7452   0.1122
  -2.000  -0.0499   0.00664   0.00095  -0.0398   0.7361   0.2189
  -1.750  -0.0224   0.00615   0.00080  -0.0402   0.7266   0.3311
  -1.500   0.0053   0.00578   0.00071  -0.0404   0.7178   0.4256
  -1.000   0.0610   0.00535   0.00065  -0.0407   0.6993   0.5602
  -0.750   0.0890   0.00524   0.00065  -0.0408   0.6902   0.6075
  -0.500   0.1173   0.00521   0.00064  -0.0409   0.6808   0.6261
  -0.250   0.1456   0.00519   0.00064  -0.0410   0.6711   0.6431
   0.000   0.1739   0.00520   0.00065  -0.0410   0.6614   0.6569
   0.250   0.2022   0.00522   0.00066  -0.0411   0.6510   0.6680
   0.500   0.2305   0.00524   0.00068  -0.0412   0.6394   0.6788
   0.750   0.2586   0.00528   0.00071  -0.0413   0.6258   0.6888
   1.000   0.2867   0.00533   0.00074  -0.0413   0.6096   0.6985
   1.250   0.3143   0.00545   0.00078  -0.0413   0.5804   0.7085
   1.500   0.3416   0.00562   0.00083  -0.0412   0.5397   0.7182
   1.750   0.3685   0.00585   0.00091  -0.0411   0.4890   0.7277
   2.000   0.3957   0.00606   0.00101  -0.0411   0.4482   0.7378
   2.250   0.4207   0.00665   0.00120  -0.0409   0.3397   0.7476
   2.500   0.4450   0.00739   0.00148  -0.0406   0.2167   0.7574
   2.750   0.4706   0.00794   0.00173  -0.0405   0.1346   0.7677
   3.000   0.4970   0.00829   0.00195  -0.0404   0.0899   0.7784
   3.250   0.5234   0.00862   0.00216  -0.0403   0.0535   0.7890
   3.500   0.5503   0.00886   0.00236  -0.0402   0.0363   0.7997
   3.750   0.5775   0.00904   0.00255  -0.0401   0.0306   0.8110
   4.000   0.6045   0.00922   0.00277  -0.0400   0.0252   0.8223
   4.250   0.6314   0.00939   0.00298  -0.0399   0.0221   0.8336
   4.500   0.6579   0.00963   0.00323  -0.0397   0.0170   0.8451
   4.750   0.6844   0.00982   0.00347  -0.0395   0.0154   0.8572
   5.000   0.7106   0.01006   0.00375  -0.0392   0.0139   0.8698
   5.250   0.7363   0.01032   0.00406  -0.0389   0.0125   0.8833
   5.500   0.7613   0.01064   0.00446  -0.0384   0.0117   0.8978
   5.750   0.7855   0.01098   0.00490  -0.0377   0.0113   0.9142
   6.000   0.8093   0.01125   0.00526  -0.0369   0.0111   0.9327
   6.250   0.8329   0.01153   0.00564  -0.0361   0.0109   0.9584
   6.500   0.8618   0.01186   0.00603  -0.0365   0.0106   1.0000
   6.750   0.8879   0.01224   0.00644  -0.0364   0.0101   1.0000
   7.000   0.9137   0.01265   0.00689  -0.0363   0.0097   1.0000
   7.250   0.9392   0.01309   0.00737  -0.0361   0.0093   1.0000
   7.500   0.9645   0.01353   0.00786  -0.0359   0.0089   1.0000
   7.750   0.9896   0.01399   0.00834  -0.0356   0.0084   1.0000
   8.000   1.0130   0.01472   0.00913  -0.0352   0.0078   1.0000
   8.250   1.0361   0.01548   0.00997  -0.0347   0.0074   1.0000
   8.500   1.0606   0.01596   0.01051  -0.0344   0.0073   1.0000
   8.750   1.0848   0.01648   0.01110  -0.0340   0.0070   1.0000
   9.000   1.1084   0.01705   0.01174  -0.0336   0.0068   1.0000
   9.250   1.1318   0.01764   0.01243  -0.0332   0.0064   1.0000
   9.500   1.1550   0.01824   0.01309  -0.0327   0.0061   1.0000
   9.750   1.1783   0.01874   0.01365  -0.0324   0.0058   1.0000
  10.000   1.2018   0.01920   0.01414  -0.0320   0.0055   1.0000
  10.250   1.2249   0.01966   0.01463  -0.0316   0.0052   1.0000
  10.500   1.2457   0.02045   0.01549  -0.0310   0.0049   1.0000
  10.750   1.2659   0.02129   0.01642  -0.0302   0.0047   1.0000
  11.000   1.2857   0.02212   0.01736  -0.0294   0.0046   1.0000
  11.250   1.3047   0.02301   0.01836  -0.0286   0.0044   1.0000
  11.500   1.3228   0.02394   0.01943  -0.0276   0.0042   1.0000
  11.750   1.3401   0.02488   0.02047  -0.0266   0.0041   1.0000
  12.000   1.3564   0.02585   0.02155  -0.0255   0.0039   1.0000
  12.250   1.3715   0.02685   0.02265  -0.0243   0.0037   1.0000
  12.500   1.3853   0.02786   0.02376  -0.0230   0.0036   1.0000
  12.750   1.3951   0.02889   0.02488  -0.0210   0.0035   1.0000
  13.000   1.4011   0.03004   0.02613  -0.0187   0.0034   1.0000
  13.250   1.4065   0.03127   0.02746  -0.0166   0.0033   1.0000
  13.500   1.4086   0.03288   0.02918  -0.0146   0.0032   1.0000
  13.750   1.4081   0.03484   0.03129  -0.0129   0.0031   1.0000
  14.000   1.4047   0.03724   0.03383  -0.0115   0.0030   1.0000
  14.250   1.3985   0.04013   0.03688  -0.0106   0.0029   1.0000
  14.500   1.3867   0.04388   0.04085  -0.0103   0.0029   1.0000
  14.750   1.3715   0.04843   0.04559  -0.0109   0.0028   1.0000
  15.000   1.3586   0.05314   0.05047  -0.0123   0.0028   1.0000
  15.250   1.3402   0.05910   0.05661  -0.0148   0.0028   1.0000
  15.500   1.3215   0.06578   0.06346  -0.0183   0.0028   1.0000
  15.750   1.2962   0.07440   0.07227  -0.0235   0.0028   1.0000
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