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NACA 64-210 (naca64210-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-210 (naca64210-il)
Reynolds number: 100,000
Max Cl/Cd: 46.36 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64210-il-100000.txt
Download as CSV file: xf-naca64210-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-210                                     
  
 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  -0.4526   0.09156   0.08694  -0.0215   1.0000   0.1337
  -9.250  -0.4493   0.08693   0.08235  -0.0217   1.0000   0.1384
  -9.000  -0.5377   0.09046   0.08559  -0.0205   1.0000   0.1292
  -8.750  -0.5578   0.08544   0.08070  -0.0267   1.0000   0.1335
  -8.500  -0.5464   0.08221   0.07748  -0.0247   1.0000   0.1413
  -8.250  -0.5640   0.07745   0.07282  -0.0293   1.0000   0.1461
  -8.000  -0.6005   0.07247   0.06773  -0.0361   1.0000   0.1487
  -7.750  -0.5823   0.06924   0.06462  -0.0337   1.0000   0.1612
  -7.500  -0.5758   0.06596   0.06138  -0.0328   1.0000   0.1722
  -7.250  -0.5767   0.06242   0.05784  -0.0330   1.0000   0.1844
  -7.000  -0.5753   0.05920   0.05460  -0.0327   1.0000   0.1986
  -6.750  -0.5713   0.05639   0.05178  -0.0317   1.0000   0.2154
  -6.250  -0.5615   0.03954   0.03255  -0.0356   1.0000   0.0917
  -6.000  -0.5454   0.03498   0.02743  -0.0335   1.0000   0.0770
  -5.750  -0.5297   0.03178   0.02395  -0.0319   1.0000   0.0733
  -5.500  -0.5131   0.02951   0.02132  -0.0301   1.0000   0.0734
  -5.250  -0.4953   0.02760   0.01907  -0.0284   1.0000   0.0744
  -5.000  -0.4759   0.02565   0.01679  -0.0268   1.0000   0.0740
  -4.750  -0.4559   0.02398   0.01487  -0.0252   1.0000   0.0745
  -4.500  -0.4355   0.02260   0.01330  -0.0237   1.0000   0.0762
  -4.250  -0.4156   0.02139   0.01195  -0.0224   1.0000   0.0807
  -4.000  -0.3962   0.02020   0.01086  -0.0211   1.0000   0.0859
  -3.750  -0.3764   0.01929   0.00989  -0.0198   1.0000   0.0913
  -3.500  -0.3576   0.01829   0.00903  -0.0186   1.0000   0.1003
  -3.250  -0.3384   0.01749   0.00830  -0.0176   1.0000   0.1157
  -3.000  -0.3179   0.01643   0.00746  -0.0170   1.0000   0.1523
  -2.750  -0.3112   0.01410   0.00776  -0.0129   1.0000   0.6738
  -2.500  -0.3004   0.01448   0.00820  -0.0089   0.9997   0.7349
  -2.250  -0.2708   0.01512   0.00880  -0.0080   0.9900   0.7870
  -2.000  -0.2533   0.01590   0.00966  -0.0035   0.9798   0.8405
  -1.750  -0.2391   0.01658   0.01037   0.0024   0.9702   0.8912
  -1.500  -0.2083   0.01675   0.01040   0.0025   0.9613   0.9170
  -1.250  -0.1579   0.01689   0.01036  -0.0023   0.9558   0.9305
  -1.000  -0.1127   0.01691   0.01024  -0.0063   0.9480   0.9427
  -0.750  -0.0526   0.01701   0.01018  -0.0132   0.9435   0.9510
  -0.500   0.0034   0.01706   0.01013  -0.0194   0.9381   0.9600
  -0.250   0.0638   0.01706   0.01005  -0.0265   0.9327   0.9677
   0.000   0.1293   0.01702   0.00995  -0.0346   0.9291   0.9736
   0.250   0.1913   0.01694   0.00985  -0.0421   0.9248   0.9805
   0.500   0.2486   0.01680   0.00973  -0.0487   0.9183   0.9884
   0.750   0.3100   0.01659   0.00955  -0.0560   0.9138   0.9953
   1.000   0.3482   0.01657   0.00959  -0.0591   0.9041   1.0000
   1.250   0.3752   0.01661   0.00966  -0.0600   0.8939   1.0000
   1.500   0.4029   0.01662   0.00972  -0.0607   0.8844   1.0000
   1.750   0.4170   0.01684   0.00998  -0.0591   0.8720   1.0000
   2.000   0.4312   0.01706   0.01028  -0.0573   0.8600   1.0000
   2.250   0.4480   0.01726   0.01052  -0.0557   0.8488   1.0000
   2.500   0.4742   0.01730   0.01063  -0.0554   0.8402   1.0000
   2.750   0.4874   0.01763   0.01102  -0.0532   0.8280   1.0000
   3.000   0.5069   0.01788   0.01137  -0.0518   0.8163   1.0000
   3.250   0.5326   0.01779   0.01138  -0.0507   0.8026   1.0000
   3.500   0.5625   0.01673   0.01037  -0.0479   0.7799   1.0000
   3.750   0.5838   0.01545   0.00904  -0.0431   0.7423   1.0000
   4.000   0.6066   0.01469   0.00826  -0.0398   0.7091   1.0000
   4.250   0.6284   0.01439   0.00804  -0.0374   0.6759   1.0000
   4.500   0.6481   0.01398   0.00759  -0.0343   0.6157   1.0000
   4.750   0.6470   0.01532   0.00720  -0.0278   0.2740   1.0000
   5.000   0.6509   0.01834   0.00891  -0.0248   0.1222   1.0000
   5.250   0.6689   0.01972   0.01021  -0.0232   0.1010   1.0000
   5.500   0.6887   0.02109   0.01149  -0.0219   0.0885   1.0000
   5.750   0.7112   0.02275   0.01299  -0.0211   0.0804   1.0000
   6.000   0.7382   0.02432   0.01462  -0.0205   0.0753   1.0000
   6.250   0.7654   0.02632   0.01652  -0.0204   0.0704   1.0000
   6.500   0.7926   0.02834   0.01878  -0.0200   0.0666   1.0000
   6.750   0.8198   0.03063   0.02136  -0.0195   0.0655   1.0000
   7.000   0.8452   0.03331   0.02442  -0.0187   0.0654   1.0000
   7.250   0.8683   0.03647   0.02796  -0.0177   0.0664   1.0000
   7.500   0.8882   0.03969   0.03161  -0.0166   0.0666   1.0000
   7.750   0.9051   0.04302   0.03538  -0.0153   0.0666   1.0000
   8.000   0.9244   0.04881   0.04129  -0.0151   0.0694   1.0000
   9.750   0.8310   0.09423   0.08982  -0.0160   0.1643   1.0000
  10.000   0.7732   0.10326   0.09871  -0.0279   0.1577   1.0000
  10.250   0.8236   0.10407   0.09962  -0.0190   0.1507   1.0000
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