Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 65(3)-218 (naca653218-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 65(3)-218 (naca653218-il)
Reynolds number: 1,000,000
Max Cl/Cd: 102.43 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca653218-il-1000000.txt
Download as CSV file: xf-naca653218-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(3)-218                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -0.9693   0.10260   0.09971  -0.0483   1.0000   0.0157
 -19.500  -0.9885   0.09557   0.09252  -0.0521   1.0000   0.0157
 -19.250  -1.0028   0.08957   0.08638  -0.0552   1.0000   0.0158
 -19.000  -1.0127   0.08441   0.08110  -0.0579   1.0000   0.0159
 -18.750  -1.0188   0.07997   0.07654  -0.0601   1.0000   0.0160
 -18.500  -1.0261   0.07549   0.07194  -0.0623   1.0000   0.0161
 -18.250  -1.0320   0.07151   0.06784  -0.0638   1.0000   0.0161
 -18.000  -1.0478   0.06649   0.06264  -0.0651   1.0000   0.0162
 -17.750  -1.0561   0.06263   0.05866  -0.0657   1.0000   0.0165
 -17.500  -1.0574   0.05965   0.05561  -0.0663   1.0000   0.0166
 -17.250  -1.0562   0.05698   0.05287  -0.0668   1.0000   0.0167
 -17.000  -1.0531   0.05457   0.05040  -0.0672   1.0000   0.0168
 -16.750  -1.0507   0.05216   0.04791  -0.0675   1.0000   0.0169
 -16.500  -1.0457   0.05006   0.04577  -0.0678   1.0000   0.0171
 -16.250  -1.0414   0.04795   0.04358  -0.0678   1.0000   0.0172
 -16.000  -1.0354   0.04601   0.04159  -0.0679   1.0000   0.0174
 -15.750  -1.0296   0.04413   0.03965  -0.0678   1.0000   0.0176
 -15.500  -1.0225   0.04241   0.03786  -0.0678   1.0000   0.0178
 -15.250  -1.0154   0.04073   0.03611  -0.0674   1.0000   0.0179
 -15.000  -1.0071   0.03917   0.03449  -0.0671   1.0000   0.0181
 -14.750  -0.9982   0.03772   0.03298  -0.0668   1.0000   0.0184
 -14.500  -0.9886   0.03636   0.03156  -0.0664   1.0000   0.0186
 -14.250  -0.9790   0.03502   0.03016  -0.0659   1.0000   0.0188
 -14.000  -0.9682   0.03382   0.02891  -0.0654   1.0000   0.0190
 -13.750  -0.9572   0.03266   0.02769  -0.0648   1.0000   0.0192
 -13.500  -0.9455   0.03158   0.02655  -0.0642   1.0000   0.0193
 -13.250  -0.9190   0.03003   0.02492  -0.0668   0.9695   0.0196
 -13.000  -0.8850   0.02830   0.02313  -0.0712   0.9560   0.0201
 -12.750  -0.8532   0.02702   0.02177  -0.0748   0.9353   0.0205
 -12.500  -0.8368   0.02612   0.02075  -0.0747   0.9113   0.0208
 -12.250  -0.8248   0.02532   0.01985  -0.0736   0.8931   0.0211
 -11.750  -0.8011   0.02372   0.01808  -0.0712   0.8658   0.0217
 -11.500  -0.7886   0.02294   0.01722  -0.0700   0.8548   0.0220
 -11.250  -0.7771   0.02214   0.01632  -0.0687   0.8443   0.0222
 -11.000  -0.7619   0.02151   0.01564  -0.0678   0.8355   0.0227
 -10.750  -0.7474   0.02088   0.01493  -0.0667   0.8268   0.0230
 -10.500  -0.7318   0.02028   0.01428  -0.0657   0.8192   0.0232
 -10.250  -0.7254   0.01922   0.01313  -0.0637   0.8107   0.0236
 -10.000  -0.7176   0.01825   0.01212  -0.0618   0.8032   0.0241
  -9.750  -0.7052   0.01756   0.01137  -0.0603   0.7956   0.0245
  -9.500  -0.6913   0.01697   0.01074  -0.0589   0.7887   0.0251
  -9.250  -0.6767   0.01640   0.01013  -0.0576   0.7822   0.0256
  -9.000  -0.6625   0.01586   0.00954  -0.0561   0.7757   0.0261
  -8.750  -0.6477   0.01536   0.00898  -0.0547   0.7700   0.0266
  -8.500  -0.6323   0.01488   0.00846  -0.0533   0.7640   0.0271
  -8.250  -0.6164   0.01449   0.00801  -0.0518   0.7582   0.0275
  -8.000  -0.6080   0.01383   0.00730  -0.0492   0.7527   0.0285
  -7.750  -0.5968   0.01337   0.00682  -0.0468   0.7470   0.0294
  -7.500  -0.5834   0.01310   0.00650  -0.0446   0.7415   0.0304
  -7.250  -0.5649   0.01281   0.00618  -0.0433   0.7366   0.0315
  -7.000  -0.5440   0.01255   0.00589  -0.0424   0.7321   0.0324
  -6.750  -0.5257   0.01216   0.00547  -0.0411   0.7274   0.0344
  -6.500  -0.5046   0.01189   0.00517  -0.0403   0.7228   0.0365
  -6.250  -0.4821   0.01162   0.00488  -0.0396   0.7188   0.0391
  -6.000  -0.4601   0.01130   0.00459  -0.0389   0.7147   0.0443
  -5.750  -0.4393   0.01090   0.00426  -0.0380   0.7104   0.0598
  -5.500  -0.4216   0.01031   0.00386  -0.0368   0.7060   0.1046
  -5.250  -0.4041   0.00960   0.00346  -0.0356   0.7021   0.1712
  -5.000  -0.3862   0.00881   0.00303  -0.0345   0.6985   0.2532
  -4.750  -0.3688   0.00790   0.00256  -0.0334   0.6947   0.3586
  -4.500  -0.3493   0.00710   0.00219  -0.0325   0.6911   0.4674
  -4.250  -0.3233   0.00689   0.00210  -0.0325   0.6872   0.5142
  -4.000  -0.2950   0.00678   0.00204  -0.0328   0.6844   0.5358
  -3.750  -0.2662   0.00673   0.00200  -0.0331   0.6811   0.5489
  -3.500  -0.2372   0.00671   0.00196  -0.0335   0.6776   0.5610
  -3.250  -0.2084   0.00671   0.00194  -0.0338   0.6743   0.5733
  -3.000  -0.1797   0.00672   0.00194  -0.0341   0.6708   0.5839
  -2.750  -0.1503   0.00675   0.00194  -0.0345   0.6683   0.5935
  -2.500  -0.1213   0.00676   0.00199  -0.0348   0.6655   0.6043
  -2.250  -0.0920   0.00678   0.00199  -0.0352   0.6626   0.6116
  -2.000  -0.0628   0.00677   0.00198  -0.0356   0.6596   0.6162
  -1.750  -0.0336   0.00679   0.00197  -0.0360   0.6566   0.6197
  -1.500  -0.0042   0.00683   0.00196  -0.0365   0.6533   0.6223
  -1.250   0.0254   0.00683   0.00194  -0.0370   0.6512   0.6246
  -1.000   0.0550   0.00682   0.00192  -0.0375   0.6487   0.6268
  -0.750   0.0844   0.00678   0.00190  -0.0379   0.6461   0.6297
  -0.500   0.1137   0.00677   0.00189  -0.0384   0.6435   0.6323
  -0.250   0.1430   0.00679   0.00189  -0.0388   0.6407   0.6349
   0.000   0.1723   0.00684   0.00191  -0.0393   0.6377   0.6375
   0.250   0.2018   0.00685   0.00193  -0.0398   0.6355   0.6399
   0.500   0.2314   0.00686   0.00194  -0.0403   0.6334   0.6421
   0.750   0.2608   0.00686   0.00195  -0.0407   0.6309   0.6448
   1.000   0.2901   0.00684   0.00197  -0.0412   0.6283   0.6478
   1.250   0.3193   0.00686   0.00199  -0.0416   0.6259   0.6506
   1.500   0.3486   0.00690   0.00203  -0.0420   0.6234   0.6532
   1.750   0.3779   0.00698   0.00209  -0.0425   0.6203   0.6559
   2.000   0.4073   0.00699   0.00213  -0.0430   0.6183   0.6585
   2.250   0.4367   0.00700   0.00217  -0.0434   0.6159   0.6611
   2.500   0.4656   0.00698   0.00220  -0.0438   0.6123   0.6646
   2.750   0.4944   0.00699   0.00223  -0.0441   0.6080   0.6677
   3.000   0.5231   0.00707   0.00229  -0.0445   0.6033   0.6707
   3.250   0.5519   0.00704   0.00231  -0.0448   0.5981   0.6737
   3.500   0.5800   0.00706   0.00231  -0.0449   0.5895   0.6766
   3.750   0.6083   0.00705   0.00234  -0.0452   0.5812   0.6799
   4.000   0.6356   0.00709   0.00238  -0.0452   0.5714   0.6835
   4.250   0.6639   0.00710   0.00243  -0.0454   0.5609   0.6871
   4.500   0.6914   0.00717   0.00250  -0.0456   0.5499   0.6907
   4.750   0.7185   0.00727   0.00257  -0.0456   0.5360   0.6940
   5.000   0.7451   0.00736   0.00266  -0.0455   0.5199   0.6977
   5.250   0.7703   0.00752   0.00279  -0.0452   0.4957   0.7016
   5.500   0.7900   0.00795   0.00302  -0.0440   0.4456   0.7056
   5.750   0.7997   0.00890   0.00355  -0.0412   0.3586   0.7096
   6.000   0.8080   0.00984   0.00412  -0.0382   0.2832   0.7137
   6.250   0.8161   0.01064   0.00466  -0.0351   0.2210   0.7186
   6.500   0.8225   0.01141   0.00519  -0.0317   0.1701   0.7234
   6.750   0.8241   0.01208   0.00567  -0.0274   0.1304   0.7282
   7.000   0.8257   0.01286   0.00629  -0.0233   0.0949   0.7334
   7.250   0.8284   0.01369   0.00700  -0.0196   0.0656   0.7388
   7.500   0.8351   0.01448   0.00768  -0.0167   0.0459   0.7443
   7.750   0.8467   0.01512   0.00829  -0.0147   0.0382   0.7495
   8.000   0.8591   0.01573   0.00893  -0.0128   0.0340   0.7554
   8.250   0.8734   0.01631   0.00953  -0.0113   0.0318   0.7616
   8.500   0.8850   0.01704   0.01028  -0.0095   0.0293   0.7677
   8.750   0.9003   0.01760   0.01090  -0.0082   0.0282   0.7741
   9.000   0.9149   0.01823   0.01157  -0.0069   0.0272   0.7808
   9.250   0.9275   0.01897   0.01234  -0.0054   0.0259   0.7873
   9.500   0.9374   0.01989   0.01332  -0.0036   0.0246   0.7947
   9.750   0.9514   0.02061   0.01409  -0.0024   0.0242   0.8017
  10.000   0.9655   0.02132   0.01487  -0.0013   0.0235   0.8095
  10.500   0.9913   0.02294   0.01659   0.0012   0.0220   0.8267
  10.750   1.0016   0.02394   0.01764   0.0026   0.0214   0.8360
  11.000   1.0069   0.02525   0.01904   0.0044   0.0207   0.8466
  11.250   1.0186   0.02616   0.02004   0.0055   0.0205   0.8573
  11.500   1.0310   0.02705   0.02100   0.0066   0.0201   0.8693
  11.750   1.0408   0.02808   0.02213   0.0080   0.0199   0.8840
  12.000   1.0519   0.02897   0.02312   0.0092   0.0193   0.9022
  12.250   1.0593   0.03007   0.02434   0.0108   0.0191   0.9315
  12.500   1.0875   0.03124   0.02563   0.0081   0.0185   0.9758
  12.750   1.0959   0.03251   0.02693   0.0092   0.0183   1.0000
  13.000   1.1054   0.03393   0.02837   0.0098   0.0180   1.0000
  13.250   1.1111   0.03568   0.03015   0.0107   0.0176   1.0000
  13.500   1.1139   0.03769   0.03222   0.0116   0.0173   1.0000
  13.750   1.1214   0.03937   0.03395   0.0122   0.0171   1.0000
  14.000   1.1339   0.04066   0.03529   0.0125   0.0169   1.0000
  14.250   1.1426   0.04229   0.03697   0.0129   0.0169   1.0000
  14.500   1.1536   0.04376   0.03849   0.0132   0.0166   1.0000
  14.750   1.1626   0.04544   0.04022   0.0134   0.0164   1.0000
  15.000   1.1734   0.04697   0.04180   0.0136   0.0161   1.0000
  15.250   1.1804   0.04888   0.04377   0.0138   0.0159   1.0000
  15.500   1.1897   0.05062   0.04555   0.0139   0.0157   1.0000
  15.750   1.1973   0.05255   0.04754   0.0139   0.0155   1.0000
  16.000   1.2055   0.05447   0.04950   0.0138   0.0153   1.0000
  16.250   1.2118   0.05660   0.05168   0.0138   0.0152   1.0000
  16.500   1.2175   0.05880   0.05395   0.0137   0.0151   1.0000
  16.750   1.2237   0.06102   0.05622   0.0135   0.0150   1.0000
  17.000   1.2284   0.06345   0.05869   0.0132   0.0148   1.0000
  17.250   1.2332   0.06590   0.06119   0.0129   0.0146   1.0000
  17.500   1.2350   0.06870   0.06405   0.0126   0.0144   1.0000
  17.750   1.2368   0.07148   0.06691   0.0123   0.0143   1.0000
  18.000   1.2365   0.07461   0.07014   0.0119   0.0141   1.0000
  18.250   1.2398   0.07745   0.07306   0.0113   0.0141   1.0000
  18.500   1.2417   0.08058   0.07629   0.0103   0.0140   1.0000
  18.750   1.2424   0.08399   0.07981   0.0091   0.0139   1.0000
  19.000   1.2436   0.08727   0.08318   0.0079   0.0138   1.0000
  19.250   1.2423   0.09104   0.08706   0.0065   0.0137   1.0000
<< Back to NACA 65(3)-218 (naca653218-il)

Polar data table (+)

Polar graphs


<< Back to NACA 65(3)-218 (naca653218-il)