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NACA 66-210 (naca66210-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 66-210 (naca66210-il)
Reynolds number: 500,000
Max Cl/Cd: 61.92 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca66210-il-500000-n5.txt
Download as CSV file: xf-naca66210-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66-210                                     
  
 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  -0.5502   0.08425   0.08199  -0.0412   1.0000   0.0066
 -10.250  -0.5456   0.08151   0.07926  -0.0431   1.0000   0.0072
 -10.000  -0.5697   0.07132   0.06910  -0.0517   1.0000   0.0069
  -9.750  -0.6286   0.06028   0.05796  -0.0557   1.0000   0.0064
  -9.500  -0.6319   0.05703   0.05463  -0.0565   0.9865   0.0066
  -9.250  -0.6240   0.05247   0.04989  -0.0597   0.9733   0.0068
  -9.000  -0.6225   0.04613   0.04324  -0.0617   0.9604   0.0071
  -8.750  -0.6235   0.03984   0.03655  -0.0611   0.9474   0.0075
  -8.500  -0.6518   0.02667   0.02224  -0.0552   0.9309   0.0083
  -8.250  -0.6420   0.02245   0.01736  -0.0530   0.9232   0.0089
  -8.000  -0.6249   0.02046   0.01505  -0.0517   0.9164   0.0094
  -7.750  -0.6023   0.02007   0.01459  -0.0513   0.9109   0.0098
  -7.500  -0.5790   0.01976   0.01420  -0.0509   0.9058   0.0103
  -7.250  -0.5558   0.01913   0.01344  -0.0504   0.9006   0.0110
  -7.000  -0.5330   0.01800   0.01208  -0.0498   0.8962   0.0117
  -6.750  -0.5096   0.01693   0.01081  -0.0492   0.8917   0.0124
  -6.500  -0.4855   0.01608   0.00981  -0.0487   0.8871   0.0129
  -6.250  -0.4625   0.01503   0.00861  -0.0481   0.8829   0.0136
  -6.000  -0.4381   0.01453   0.00806  -0.0478   0.8788   0.0145
  -5.750  -0.4131   0.01417   0.00764  -0.0475   0.8743   0.0154
  -5.500  -0.3885   0.01363   0.00703  -0.0471   0.8702   0.0161
  -5.250  -0.3641   0.01307   0.00639  -0.0467   0.8668   0.0168
  -5.000  -0.3396   0.01255   0.00580  -0.0463   0.8629   0.0175
  -4.750  -0.3145   0.01216   0.00536  -0.0459   0.8590   0.0184
  -4.500  -0.2888   0.01188   0.00500  -0.0457   0.8556   0.0191
  -4.250  -0.2658   0.01118   0.00423  -0.0450   0.8525   0.0204
  -4.000  -0.2408   0.01077   0.00380  -0.0447   0.8488   0.0220
  -3.750  -0.2151   0.01048   0.00348  -0.0445   0.8450   0.0236
  -3.500  -0.1890   0.01023   0.00317  -0.0443   0.8417   0.0256
  -3.250  -0.1626   0.01003   0.00291  -0.0442   0.8389   0.0274
  -3.000  -0.1360   0.00983   0.00268  -0.0441   0.8360   0.0299
  -2.750  -0.1096   0.00958   0.00244  -0.0440   0.8328   0.0353
  -2.500  -0.0828   0.00942   0.00224  -0.0440   0.8298   0.0399
  -2.250  -0.0563   0.00918   0.00208  -0.0439   0.8271   0.0603
  -2.000  -0.0337   0.00839   0.00184  -0.0436   0.8244   0.2236
  -1.750  -0.0143   0.00717   0.00156  -0.0429   0.8211   0.4874
  -1.500   0.0062   0.00643   0.00157  -0.0418   0.8178   0.6956
  -1.250   0.0318   0.00639   0.00168  -0.0412   0.8151   0.7521
  -1.000   0.0587   0.00641   0.00175  -0.0409   0.8127   0.7730
  -0.750   0.0866   0.00644   0.00176  -0.0409   0.8106   0.7836
  -0.500   0.1144   0.00647   0.00178  -0.0410   0.8082   0.7927
  -0.250   0.1416   0.00651   0.00185  -0.0408   0.8053   0.8038
   0.000   0.1699   0.00653   0.00186  -0.0410   0.8026   0.8091
   0.250   0.1982   0.00653   0.00188  -0.0412   0.8001   0.8115
   0.500   0.2263   0.00654   0.00188  -0.0414   0.7969   0.8139
   0.750   0.2540   0.00653   0.00188  -0.0414   0.7904   0.8164
   1.000   0.2814   0.00652   0.00183  -0.0413   0.7798   0.8191
   1.250   0.3088   0.00651   0.00182  -0.0412   0.7689   0.8220
   1.500   0.3363   0.00651   0.00183  -0.0412   0.7587   0.8249
   1.750   0.3631   0.00651   0.00184  -0.0410   0.7447   0.8274
   2.000   0.3890   0.00654   0.00183  -0.0405   0.7190   0.8302
   2.250   0.4130   0.00667   0.00179  -0.0397   0.6647   0.8334
   2.500   0.4218   0.00791   0.00205  -0.0362   0.4429   0.8376
   2.750   0.4339   0.00920   0.00251  -0.0339   0.2427   0.8411
   3.000   0.4523   0.01002   0.00286  -0.0326   0.1218   0.8447
   3.250   0.4733   0.01065   0.00320  -0.0316   0.0476   0.8488
   3.500   0.4982   0.01094   0.00344  -0.0313   0.0355   0.8528
   3.750   0.5231   0.01115   0.00369  -0.0309   0.0317   0.8559
   4.000   0.5474   0.01143   0.00397  -0.0304   0.0273   0.8595
   4.250   0.5715   0.01177   0.00438  -0.0298   0.0243   0.8636
   4.500   0.5964   0.01202   0.00467  -0.0294   0.0227   0.8676
   4.750   0.6201   0.01232   0.00503  -0.0288   0.0210   0.8713
   5.000   0.6435   0.01265   0.00540  -0.0281   0.0194   0.8757
   5.250   0.6665   0.01307   0.00586  -0.0274   0.0180   0.8808
   5.500   0.6863   0.01372   0.00658  -0.0261   0.0168   0.8855
   5.750   0.7066   0.01435   0.00729  -0.0248   0.0162   0.8909
   6.000   0.7292   0.01478   0.00779  -0.0241   0.0157   0.8962
   6.250   0.7506   0.01524   0.00833  -0.0230   0.0150   0.9014
   6.500   0.7716   0.01584   0.00902  -0.0220   0.0145   0.9074
   6.750   0.7922   0.01650   0.00978  -0.0209   0.0141   0.9132
   7.000   0.8129   0.01717   0.01053  -0.0198   0.0136   0.9198
   7.250   0.8339   0.01790   0.01136  -0.0188   0.0132   0.9267
   7.500   0.8545   0.01848   0.01203  -0.0177   0.0127   0.9347
   7.750   0.8752   0.01897   0.01258  -0.0167   0.0122   0.9435
   8.000   0.8959   0.01968   0.01337  -0.0158   0.0116   0.9539
   8.500   0.9464   0.02238   0.01645  -0.0161   0.0107   0.9781
   8.750   0.9706   0.02382   0.01811  -0.0161   0.0102   1.0000
   9.000   0.9912   0.02513   0.01961  -0.0154   0.0097   1.0000
   9.250   1.0107   0.02628   0.02092  -0.0145   0.0091   1.0000
   9.500   1.0293   0.02725   0.02203  -0.0136   0.0087   1.0000
   9.750   1.0475   0.02781   0.02270  -0.0127   0.0083   1.0000
  10.000   1.0640   0.02864   0.02362  -0.0116   0.0081   1.0000
  10.250   1.0784   0.02967   0.02478  -0.0102   0.0078   1.0000
  10.500   1.0812   0.03245   0.02786  -0.0075   0.0074   1.0000
  10.750   1.0829   0.03512   0.03089  -0.0044   0.0073   1.0000
  11.000   1.0719   0.03911   0.03531  -0.0002   0.0071   1.0000
  11.250   1.0227   0.04812   0.04499   0.0066   0.0067   1.0000
  11.500   0.9752   0.05632   0.05360   0.0107   0.0066   1.0000
  11.750   0.9437   0.06242   0.05992   0.0118   0.0066   1.0000
  12.000   0.9097   0.06967   0.06736   0.0107   0.0066   1.0000
  12.250   0.8801   0.07748   0.07529   0.0072   0.0067   1.0000
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