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

NACA 65-210 (naca65210-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 65-210 (naca65210-il)
Reynolds number: 500,000
Max Cl/Cd: 62.73 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca65210-il-500000-n5.txt
Download as CSV file: xf-naca65210-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5774   0.08645   0.08418  -0.0285   1.0000   0.0070
 -10.250  -0.5903   0.07868   0.07644  -0.0336   1.0000   0.0070
 -10.000  -0.6148   0.06765   0.06542  -0.0435   1.0000   0.0069
  -9.750  -0.6693   0.05724   0.05485  -0.0482   1.0000   0.0065
  -9.500  -0.6786   0.05442   0.05194  -0.0472   1.0000   0.0067
  -9.250  -0.6910   0.04966   0.04701  -0.0463   1.0000   0.0068
  -9.000  -0.7059   0.04347   0.04052  -0.0445   1.0000   0.0069
  -8.750  -0.7158   0.03755   0.03427  -0.0418   1.0000   0.0072
  -8.500  -0.7238   0.02392   0.01927  -0.0410   0.9857   0.0084
  -8.250  -0.6982   0.02123   0.01611  -0.0418   0.9780   0.0088
  -8.000  -0.6706   0.01952   0.01417  -0.0428   0.9708   0.0094
  -7.750  -0.6397   0.01893   0.01350  -0.0442   0.9643   0.0099
  -7.500  -0.6101   0.01868   0.01320  -0.0451   0.9560   0.0105
  -7.250  -0.5821   0.01785   0.01222  -0.0456   0.9478   0.0114
  -7.000  -0.5560   0.01687   0.01105  -0.0457   0.9386   0.0121
  -6.750  -0.5309   0.01605   0.01004  -0.0454   0.9292   0.0126
  -6.500  -0.5074   0.01499   0.00883  -0.0449   0.9200   0.0133
  -6.250  -0.4835   0.01433   0.00810  -0.0444   0.9106   0.0142
  -6.000  -0.4582   0.01401   0.00774  -0.0441   0.9017   0.0150
  -5.750  -0.4333   0.01359   0.00724  -0.0438   0.8934   0.0159
  -5.500  -0.4088   0.01303   0.00658  -0.0433   0.8847   0.0167
  -5.250  -0.3841   0.01252   0.00597  -0.0429   0.8768   0.0174
  -5.000  -0.3589   0.01209   0.00545  -0.0425   0.8689   0.0181
  -4.750  -0.3329   0.01182   0.00512  -0.0423   0.8615   0.0188
  -4.500  -0.3092   0.01108   0.00429  -0.0418   0.8535   0.0203
  -4.250  -0.2834   0.01069   0.00384  -0.0415   0.8461   0.0216
  -4.000  -0.2572   0.01040   0.00349  -0.0414   0.8388   0.0230
  -3.750  -0.2306   0.01014   0.00317  -0.0412   0.8321   0.0248
  -3.500  -0.2038   0.00992   0.00289  -0.0411   0.8250   0.0266
  -3.250  -0.1770   0.00970   0.00260  -0.0411   0.8181   0.0292
  -3.000  -0.1501   0.00946   0.00234  -0.0410   0.8110   0.0346
  -2.750  -0.1229   0.00930   0.00214  -0.0410   0.8047   0.0398
  -2.500  -0.0959   0.00904   0.00195  -0.0410   0.7981   0.0626
  -2.250  -0.0708   0.00836   0.00168  -0.0410   0.7919   0.1893
  -2.000  -0.0469   0.00733   0.00139  -0.0411   0.7850   0.4008
  -1.500   0.0034   0.00644   0.00136  -0.0406   0.7725   0.6636
  -1.250   0.0308   0.00640   0.00136  -0.0404   0.7666   0.6889
  -1.000   0.0587   0.00639   0.00135  -0.0405   0.7606   0.7019
  -0.750   0.0865   0.00638   0.00135  -0.0404   0.7544   0.7170
  -0.500   0.1144   0.00639   0.00134  -0.0405   0.7488   0.7265
  -0.250   0.1427   0.00639   0.00133  -0.0406   0.7426   0.7330
   0.000   0.1708   0.00641   0.00133  -0.0407   0.7369   0.7391
   0.250   0.1990   0.00641   0.00135  -0.0408   0.7310   0.7453
   0.500   0.2272   0.00644   0.00136  -0.0409   0.7250   0.7517
   0.750   0.2552   0.00645   0.00139  -0.0410   0.7193   0.7577
   1.000   0.2834   0.00647   0.00143  -0.0411   0.7131   0.7644
   1.250   0.3112   0.00650   0.00148  -0.0411   0.7071   0.7705
   1.500   0.3387   0.00654   0.00152  -0.0411   0.6939   0.7772
   1.750   0.3659   0.00659   0.00155  -0.0409   0.6764   0.7834
   2.000   0.3927   0.00665   0.00161  -0.0407   0.6553   0.7904
   2.250   0.4186   0.00679   0.00164  -0.0403   0.6208   0.7973
   2.500   0.4429   0.00706   0.00171  -0.0396   0.5574   0.8043
   2.750   0.4617   0.00797   0.00196  -0.0383   0.3950   0.8115
   3.000   0.4807   0.00903   0.00241  -0.0372   0.2400   0.8194
   3.250   0.5012   0.00995   0.00282  -0.0364   0.1140   0.8273
   3.500   0.5240   0.01056   0.00317  -0.0358   0.0486   0.8355
   3.750   0.5491   0.01086   0.00344  -0.0354   0.0360   0.8430
   4.000   0.5748   0.01110   0.00373  -0.0351   0.0308   0.8512
   4.250   0.5996   0.01137   0.00403  -0.0346   0.0266   0.8594
   4.500   0.6237   0.01175   0.00447  -0.0340   0.0230   0.8683
   4.750   0.6483   0.01200   0.00479  -0.0335   0.0218   0.8776
   5.000   0.6722   0.01231   0.00519  -0.0328   0.0202   0.8867
   5.250   0.6956   0.01266   0.00560  -0.0321   0.0189   0.8969
   5.500   0.7183   0.01303   0.00603  -0.0312   0.0177   0.9082
   5.750   0.7393   0.01352   0.00659  -0.0300   0.0167   0.9205
   6.000   0.7575   0.01433   0.00750  -0.0284   0.0157   0.9347
   6.250   0.7794   0.01478   0.00805  -0.0274   0.0153   0.9508
   6.500   0.8063   0.01527   0.00862  -0.0276   0.0147   0.9701
   6.750   0.8333   0.01596   0.00938  -0.0279   0.0142   1.0000
   7.000   0.8561   0.01671   0.01021  -0.0273   0.0138   1.0000
   7.250   0.8788   0.01750   0.01107  -0.0268   0.0133   1.0000
   7.500   0.9017   0.01825   0.01189  -0.0263   0.0128   1.0000
   7.750   0.9252   0.01881   0.01252  -0.0259   0.0122   1.0000
   8.000   0.9484   0.01933   0.01307  -0.0256   0.0116   1.0000
   8.250   0.9697   0.02028   0.01409  -0.0249   0.0111   1.0000
   8.500   0.9888   0.02205   0.01602  -0.0240   0.0106   1.0000
   8.750   1.0105   0.02301   0.01714  -0.0233   0.0103   1.0000
   9.000   1.0311   0.02420   0.01850  -0.0226   0.0099   1.0000
   9.250   1.0510   0.02541   0.01991  -0.0218   0.0094   1.0000
   9.500   1.0700   0.02655   0.02122  -0.0209   0.0089   1.0000
   9.750   1.0884   0.02753   0.02234  -0.0200   0.0084   1.0000
  10.000   1.1063   0.02829   0.02319  -0.0191   0.0081   1.0000
  10.250   1.1224   0.02929   0.02432  -0.0179   0.0078   1.0000
  10.500   1.1371   0.03028   0.02541  -0.0167   0.0076   1.0000
  10.750   1.1476   0.03171   0.02699  -0.0150   0.0073   1.0000
  11.000   1.1461   0.03448   0.03007  -0.0119   0.0071   1.0000
  11.250   1.1438   0.03708   0.03298  -0.0089   0.0069   1.0000
  11.500   1.1321   0.04067   0.03693  -0.0056   0.0068   1.0000
  11.750   1.1127   0.04507   0.04170  -0.0026   0.0066   1.0000
  12.000   1.0780   0.05148   0.04851  -0.0004   0.0065   1.0000
  12.250   1.0363   0.05944   0.05682  -0.0004   0.0064   1.0000
<< Back to NACA 65-210 (naca65210-il)

Polar data table (+)

Polar graphs


<< Back to NACA 65-210 (naca65210-il)