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NACA 65-210 (naca65210-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 65-210 (naca65210-il)
Reynolds number: 100,000
Max Cl/Cd: 43.34 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca65210-il-100000.txt
Download as CSV file: xf-naca65210-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-210                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5212   0.09680   0.09186  -0.0253   1.0000   0.1107
  -9.250  -0.5374   0.09234   0.08750  -0.0307   1.0000   0.1150
  -9.000  -0.5656   0.08721   0.08247  -0.0380   1.0000   0.1158
  -8.750  -0.5314   0.08455   0.07979  -0.0314   1.0000   0.1239
  -8.500  -0.5517   0.07966   0.07500  -0.0364   1.0000   0.1276
  -8.250  -0.5840   0.07589   0.07120  -0.0401   1.0000   0.1295
  -8.000  -0.5685   0.07190   0.06729  -0.0381   1.0000   0.1359
  -7.750  -0.5889   0.06880   0.06409  -0.0396   1.0000   0.1432
  -7.500  -0.5808   0.06500   0.06037  -0.0381   1.0000   0.1501
  -7.000  -0.6098   0.06131   0.05625  -0.0356   1.0000   0.1729
  -5.250  -0.5405   0.03365   0.02594  -0.0228   1.0000   0.0859
  -5.000  -0.5195   0.03156   0.02305  -0.0204   1.0000   0.0747
  -4.750  -0.5000   0.02846   0.01977  -0.0193   1.0000   0.0725
  -4.500  -0.4796   0.02672   0.01771  -0.0179   1.0000   0.0729
  -4.250  -0.4588   0.02565   0.01628  -0.0166   1.0000   0.0746
  -4.000  -0.4366   0.02415   0.01457  -0.0155   1.0000   0.0748
  -3.750  -0.4140   0.02241   0.01275  -0.0145   1.0000   0.0760
  -3.500  -0.3931   0.02111   0.01151  -0.0135   1.0000   0.0787
  -3.250  -0.3731   0.02035   0.01076  -0.0124   1.0000   0.0859
  -3.000  -0.3535   0.01943   0.00988  -0.0112   1.0000   0.0912
  -2.750  -0.3339   0.01871   0.00921  -0.0102   1.0000   0.0992
  -2.500  -0.3019   0.01789   0.00845  -0.0117   0.9963   0.1227
  -2.250  -0.2895   0.01521   0.00879  -0.0081   0.9923   0.7316
  -2.000  -0.2793   0.01615   0.00989  -0.0014   0.9844   0.8338
  -1.750  -0.2707   0.01680   0.01054   0.0050   0.9764   0.8885
  -1.500  -0.1744   0.01845   0.01187  -0.0023   0.9829   0.9644
  -1.250  -0.1201   0.01849   0.01169  -0.0086   0.9790   0.9729
  -1.000  -0.0654   0.01853   0.01154  -0.0151   0.9748   0.9794
  -0.750  -0.0098   0.01859   0.01147  -0.0218   0.9711   0.9857
  -0.500   0.0419   0.01860   0.01138  -0.0279   0.9668   0.9924
  -0.250   0.0936   0.01860   0.01130  -0.0340   0.9621   0.9994
   0.000   0.1343   0.01868   0.01133  -0.0380   0.9563   1.0000
   0.250   0.1554   0.01874   0.01138  -0.0384   0.9466   1.0000
   0.500   0.1906   0.01886   0.01149  -0.0412   0.9404   1.0000
   0.750   0.2098   0.01898   0.01161  -0.0411   0.9309   1.0000
   1.000   0.2302   0.01915   0.01179  -0.0411   0.9223   1.0000
   1.250   0.2604   0.01931   0.01198  -0.0427   0.9152   1.0000
   1.500   0.2696   0.01954   0.01224  -0.0405   0.9050   1.0000
   1.750   0.3090   0.01973   0.01249  -0.0435   0.8997   1.0000
   2.000   0.3130   0.02001   0.01278  -0.0403   0.8886   1.0000
   2.250   0.3357   0.02030   0.01313  -0.0401   0.8803   1.0000
   2.500   0.3699   0.02052   0.01346  -0.0419   0.8728   1.0000
   2.750   0.3908   0.02085   0.01385  -0.0413   0.8628   1.0000
   3.000   0.4417   0.02085   0.01405  -0.0454   0.8568   1.0000
   3.250   0.4635   0.02113   0.01444  -0.0447   0.8453   1.0000
   3.500   0.5704   0.01641   0.01010  -0.0487   0.7931   1.0000
   3.750   0.5928   0.01492   0.00863  -0.0439   0.7522   1.0000
   4.000   0.6077   0.01410   0.00782  -0.0391   0.7030   1.0000
   4.250   0.6059   0.01398   0.00659  -0.0303   0.4343   1.0000
   4.500   0.5943   0.01732   0.00784  -0.0246   0.1279   1.0000
   4.750   0.6091   0.01866   0.00898  -0.0225   0.1012   1.0000
   5.000   0.6262   0.01986   0.01011  -0.0208   0.0887   1.0000
   5.250   0.6461   0.02116   0.01132  -0.0195   0.0815   1.0000
   5.500   0.6708   0.02283   0.01292  -0.0188   0.0768   1.0000
   5.750   0.6972   0.02416   0.01432  -0.0184   0.0704   1.0000
   6.000   0.7266   0.02624   0.01635  -0.0185   0.0674   1.0000
   6.250   0.7578   0.02912   0.01931  -0.0188   0.0662   1.0000
   6.500   0.7857   0.03155   0.02202  -0.0184   0.0664   1.0000
   6.750   0.8102   0.03470   0.02549  -0.0177   0.0657   1.0000
   7.000   0.8316   0.03688   0.02815  -0.0164   0.0649   1.0000
   7.250   0.8529   0.03954   0.03164  -0.0140   0.0710   1.0000
   7.500   0.8732   0.04545   0.03776  -0.0133   0.0784   1.0000
   9.500   0.7796   0.08997   0.08551  -0.0125   0.1697   1.0000
   9.750   0.8003   0.09283   0.08840  -0.0094   0.1597   1.0000
  10.000   0.7577   0.10091   0.09635  -0.0186   0.1550   1.0000
  10.250   0.6845   0.10121   0.09702  -0.0104   0.1610   1.0000
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