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NACA 64-210 (naca64210-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-210 (naca64210-il)
Reynolds number: 200,000
Max Cl/Cd: 61.79 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64210-il-200000.txt
Download as CSV file: xf-naca64210-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4661   0.09876   0.09542  -0.0227   1.0000   0.0523
 -10.250  -0.4766   0.09283   0.08951  -0.0271   1.0000   0.0525
 -10.000  -0.4877   0.08627   0.08296  -0.0317   1.0000   0.0526
  -9.750  -0.4655   0.08424   0.08093  -0.0250   1.0000   0.0555
  -9.500  -0.4633   0.08036   0.07707  -0.0257   1.0000   0.0571
  -9.250  -0.4671   0.07549   0.07222  -0.0276   1.0000   0.0585
  -9.000  -0.4762   0.06979   0.06655  -0.0306   1.0000   0.0597
  -8.750  -0.4946   0.06254   0.05933  -0.0361   1.0000   0.0598
  -8.500  -0.5204   0.05635   0.05312  -0.0405   1.0000   0.0594
  -8.250  -0.5421   0.05196   0.04868  -0.0416   1.0000   0.0595
  -8.000  -0.5539   0.04748   0.04408  -0.0423   1.0000   0.0609
  -7.750  -0.5705   0.04424   0.04037  -0.0422   1.0000   0.0650
  -7.250  -0.6060   0.04713   0.04257  -0.0408   1.0000   0.0676
  -7.000  -0.5933   0.04428   0.03977  -0.0398   1.0000   0.0698
  -6.750  -0.5831   0.04204   0.03743  -0.0383   1.0000   0.0738
  -6.500  -0.5806   0.03949   0.03445  -0.0360   1.0000   0.0816
  -6.250  -0.5701   0.03720   0.03221  -0.0342   1.0000   0.0845
  -6.000  -0.5561   0.02994   0.02385  -0.0299   1.0000   0.0491
  -5.750  -0.5430   0.02707   0.02062  -0.0277   1.0000   0.0470
  -5.500  -0.5256   0.02387   0.01673  -0.0252   1.0000   0.0424
  -5.250  -0.5027   0.02219   0.01478  -0.0244   0.9991   0.0419
  -5.000  -0.4654   0.01998   0.01237  -0.0264   0.9953   0.0427
  -4.750  -0.4282   0.01870   0.01104  -0.0287   0.9905   0.0464
  -4.500  -0.3898   0.01745   0.00968  -0.0309   0.9858   0.0491
  -4.250  -0.3512   0.01638   0.00853  -0.0330   0.9812   0.0519
  -4.000  -0.3162   0.01503   0.00720  -0.0349   0.9750   0.0571
  -3.750  -0.2752   0.01431   0.00645  -0.0379   0.9707   0.0659
  -3.500  -0.2400   0.01332   0.00551  -0.0399   0.9637   0.0816
  -3.250  -0.2093   0.01042   0.00459  -0.0426   0.9583   0.4980
  -3.000  -0.1762   0.01017   0.00471  -0.0433   0.9515   0.6298
  -2.750  -0.1411   0.01016   0.00472  -0.0444   0.9446   0.6718
  -2.500  -0.1083   0.01019   0.00476  -0.0450   0.9373   0.7024
  -2.250  -0.0791   0.01037   0.00499  -0.0443   0.9293   0.7426
  -2.000  -0.0551   0.01062   0.00533  -0.0423   0.9199   0.7740
  -1.750  -0.0250   0.01061   0.00526  -0.0423   0.9127   0.7875
  -1.500   0.0006   0.01059   0.00520  -0.0415   0.9021   0.7982
  -1.250   0.0271   0.01056   0.00514  -0.0409   0.8931   0.8075
  -1.000   0.0542   0.01051   0.00503  -0.0405   0.8846   0.8172
  -0.750   0.0793   0.01049   0.00498  -0.0397   0.8743   0.8270
  -0.500   0.1047   0.01046   0.00493  -0.0389   0.8656   0.8362
  -0.250   0.1302   0.01043   0.00487  -0.0382   0.8566   0.8463
   0.000   0.1551   0.01043   0.00487  -0.0374   0.8471   0.8572
   0.250   0.1797   0.01040   0.00483  -0.0363   0.8395   0.8670
   0.500   0.2035   0.01040   0.00485  -0.0353   0.8294   0.8779
   0.750   0.2280   0.01040   0.00485  -0.0344   0.8211   0.8894
   1.000   0.2521   0.01039   0.00485  -0.0334   0.8128   0.9018
   1.250   0.2756   0.01040   0.00489  -0.0322   0.8037   0.9145
   1.500   0.3010   0.01036   0.00486  -0.0314   0.7966   0.9270
   1.750   0.3277   0.01036   0.00491  -0.0310   0.7873   0.9402
   2.000   0.3593   0.01033   0.00490  -0.0316   0.7791   0.9525
   2.250   0.3952   0.01030   0.00492  -0.0332   0.7695   0.9635
   2.500   0.4343   0.01030   0.00499  -0.0356   0.7598   0.9738
   2.750   0.4738   0.01017   0.00488  -0.0377   0.7443   0.9836
   3.000   0.5132   0.00977   0.00436  -0.0392   0.7093   0.9922
   3.250   0.5452   0.00964   0.00419  -0.0400   0.6789   1.0000
   3.500   0.5620   0.00966   0.00424  -0.0381   0.6589   1.0000
   3.750   0.5807   0.00971   0.00425  -0.0364   0.6319   1.0000
   4.000   0.6022   0.00981   0.00429  -0.0351   0.5949   1.0000
   4.250   0.6228   0.01008   0.00433  -0.0336   0.5181   1.0000
   4.750   0.6397   0.01435   0.00616  -0.0287   0.0765   1.0000
   5.000   0.6615   0.01527   0.00706  -0.0279   0.0627   1.0000
   5.250   0.6813   0.01650   0.00825  -0.0269   0.0557   1.0000
   5.500   0.7046   0.01731   0.00911  -0.0262   0.0503   1.0000
   5.750   0.7259   0.01855   0.01028  -0.0254   0.0457   1.0000
   6.000   0.7489   0.02017   0.01193  -0.0247   0.0435   1.0000
   6.250   0.7745   0.02146   0.01334  -0.0241   0.0420   1.0000
   6.500   0.8008   0.02303   0.01504  -0.0237   0.0408   1.0000
   6.750   0.8264   0.02445   0.01659  -0.0233   0.0387   1.0000
   7.000   0.8514   0.02606   0.01832  -0.0229   0.0370   1.0000
   7.250   0.8765   0.02834   0.02085  -0.0224   0.0367   1.0000
   7.500   0.8989   0.03172   0.02475  -0.0211   0.0381   1.0000
   7.750   0.9169   0.03643   0.03001  -0.0194   0.0415   1.0000
   8.750   0.9433   0.05810   0.05385  -0.0107   0.0653   1.0000
   9.000   0.9429   0.06131   0.05731  -0.0093   0.0622   1.0000
   9.250   0.9444   0.06457   0.06069  -0.0084   0.0602   1.0000
   9.500   0.9524   0.06797   0.06409  -0.0079   0.0586   1.0000
   9.750   0.8126   0.06678   0.06359  -0.0022   0.0638   1.0000
  10.000   0.7806   0.07306   0.06998  -0.0042   0.0646   1.0000
  10.250   0.7496   0.08080   0.07778  -0.0081   0.0656   1.0000
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