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NACA 65-209 (naca65209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 65-209 (naca65209-il)
Reynolds number: 1,000,000
Max Cl/Cd: 80.63 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca65209-il-1000000.txt
Download as CSV file: xf-naca65209-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-209                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.5821   0.04972   0.04770  -0.0419   1.0000   0.0110
  -7.500  -0.5841   0.04568   0.04350  -0.0398   1.0000   0.0110
  -7.250  -0.5701   0.03953   0.03704  -0.0414   0.9956   0.0111
  -7.000  -0.5636   0.02821   0.02502  -0.0441   0.9868   0.0092
  -6.750  -0.5406   0.01983   0.01580  -0.0447   0.9818   0.0092
  -6.500  -0.5126   0.01761   0.01329  -0.0453   0.9753   0.0099
  -6.250  -0.4819   0.01588   0.01129  -0.0462   0.9701   0.0107
  -5.750  -0.4307   0.01253   0.00750  -0.0459   0.9528   0.0121
  -5.500  -0.4056   0.01193   0.00684  -0.0455   0.9434   0.0127
  -5.250  -0.3804   0.01150   0.00636  -0.0451   0.9341   0.0135
  -5.000  -0.3550   0.01113   0.00593  -0.0447   0.9254   0.0146
  -4.750  -0.3294   0.01082   0.00554  -0.0443   0.9163   0.0156
  -4.500  -0.3035   0.01048   0.00514  -0.0439   0.9077   0.0162
  -4.000  -0.2551   0.00887   0.00332  -0.0428   0.8905   0.0184
  -3.750  -0.2287   0.00862   0.00302  -0.0426   0.8825   0.0203
  -3.500  -0.2020   0.00837   0.00272  -0.0425   0.8742   0.0221
  -3.250  -0.1751   0.00814   0.00245  -0.0424   0.8664   0.0235
  -3.000  -0.1480   0.00796   0.00221  -0.0422   0.8587   0.0247
  -2.750  -0.1212   0.00758   0.00176  -0.0421   0.8508   0.0308
  -2.250  -0.0669   0.00710   0.00135  -0.0421   0.8354   0.0774
  -2.000  -0.0431   0.00588   0.00104  -0.0422   0.8281   0.3568
  -1.750  -0.0182   0.00504   0.00090  -0.0422   0.8202   0.5738
  -1.500   0.0089   0.00487   0.00087  -0.0422   0.8132   0.6342
  -1.250   0.0364   0.00478   0.00086  -0.0421   0.8056   0.6728
  -1.000   0.0637   0.00471   0.00088  -0.0420   0.7987   0.7112
  -0.750   0.0914   0.00470   0.00089  -0.0420   0.7912   0.7341
  -0.500   0.1191   0.00469   0.00090  -0.0419   0.7843   0.7504
  -0.250   0.1469   0.00469   0.00091  -0.0419   0.7769   0.7643
   0.000   0.1750   0.00470   0.00092  -0.0420   0.7701   0.7726
   0.250   0.2031   0.00471   0.00093  -0.0421   0.7627   0.7800
   0.500   0.2312   0.00473   0.00094  -0.0422   0.7555   0.7880
   0.750   0.2590   0.00474   0.00096  -0.0422   0.7470   0.7953
   1.000   0.2869   0.00477   0.00098  -0.0422   0.7346   0.8034
   1.250   0.3140   0.00480   0.00100  -0.0420   0.7184   0.8108
   1.500   0.3414   0.00486   0.00102  -0.0419   0.6983   0.8188
   1.750   0.3681   0.00493   0.00105  -0.0417   0.6728   0.8267
   2.000   0.3947   0.00505   0.00109  -0.0414   0.6384   0.8347
   2.250   0.4209   0.00522   0.00117  -0.0411   0.5988   0.8431
   2.500   0.4452   0.00558   0.00128  -0.0406   0.5200   0.8512
   2.750   0.4640   0.00677   0.00165  -0.0394   0.3121   0.8607
   3.250   0.5060   0.00859   0.00243  -0.0377   0.0389   0.8793
   3.500   0.5314   0.00893   0.00279  -0.0372   0.0283   0.8889
   3.750   0.5570   0.00909   0.00300  -0.0368   0.0255   0.8986
   4.000   0.5816   0.00938   0.00332  -0.0362   0.0217   0.9086
   4.250   0.6043   0.00995   0.00402  -0.0352   0.0192   0.9194
   4.500   0.6286   0.01019   0.00432  -0.0345   0.0186   0.9305
   4.750   0.6513   0.01049   0.00468  -0.0335   0.0177   0.9430
   5.000   0.6729   0.01081   0.00509  -0.0322   0.0168   0.9584
   5.250   0.6998   0.01114   0.00546  -0.0322   0.0156   0.9769
   5.500   0.7303   0.01162   0.00596  -0.0332   0.0144   1.0000
   5.750   0.7528   0.01263   0.00704  -0.0325   0.0136   1.0000
   6.000   0.7725   0.01447   0.00900  -0.0313   0.0129   1.0000
   6.250   0.7983   0.01498   0.00957  -0.0311   0.0126   1.0000
   6.500   0.8240   0.01550   0.01014  -0.0309   0.0121   1.0000
   6.750   0.8496   0.01594   0.01064  -0.0307   0.0113   1.0000
   7.000   0.8742   0.01671   0.01149  -0.0304   0.0106   1.0000
   7.250   0.8984   0.01752   0.01238  -0.0300   0.0101   1.0000
   7.500   0.9224   0.01822   0.01314  -0.0297   0.0097   1.0000
   7.750   0.9455   0.01918   0.01418  -0.0292   0.0092   1.0000
   8.250   0.9800   0.02504   0.02071  -0.0266   0.0083   1.0000
   8.500   1.0010   0.02625   0.02210  -0.0257   0.0078   1.0000
   8.750   1.0163   0.02897   0.02515  -0.0242   0.0072   1.0000
   9.000   1.0075   0.03764   0.03454  -0.0197   0.0069   1.0000
   9.250   0.9888   0.04678   0.04424  -0.0151   0.0070   1.0000
   9.500   0.9718   0.05345   0.05124  -0.0117   0.0073   1.0000
   9.750   0.9550   0.05859   0.05659  -0.0090   0.0073   1.0000
  10.000   0.9304   0.06224   0.06038  -0.0055   0.0076   1.0000
  10.250   0.9061   0.06618   0.06444  -0.0043   0.0078   1.0000
  10.500   0.8843   0.07130   0.06966  -0.0052   0.0078   1.0000
  10.750   0.8581   0.07760   0.07606  -0.0086   0.0080   1.0000
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