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NACA 65-206 (naca65206-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 65-206 (naca65206-il)
Reynolds number: 50,000
Max Cl/Cd: 22.19 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca65206-il-50000.txt
Download as CSV file: xf-naca65206-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-206                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5589   0.10390   0.09710   0.0010   1.0000   0.2108
  -8.250  -0.5555   0.10059   0.09384   0.0010   1.0000   0.2262
  -8.000  -0.5571   0.09777   0.09111   0.0007   1.0000   0.2430
  -7.750  -0.5495   0.09420   0.08759   0.0022   1.0000   0.2680
  -7.500  -0.5441   0.09096   0.08440   0.0037   1.0000   0.2941
  -7.250  -0.5394   0.08794   0.08144   0.0053   1.0000   0.3220
  -7.000  -0.5424   0.08556   0.07917   0.0071   1.0000   0.3517
  -6.750  -0.5297   0.08226   0.07588   0.0104   1.0000   0.3917
  -6.500  -0.5090   0.07862   0.07224   0.0145   1.0000   0.4444
  -6.250  -0.4996   0.07613   0.06980   0.0190   1.0000   0.5001
  -6.000  -0.4550   0.07107   0.06454   0.0228   1.0000   0.5778
  -5.750  -0.4222   0.06672   0.06016   0.0248   1.0000   0.6432
  -5.000  -0.4023   0.05771   0.05132   0.0261   1.0000   0.6781
  -4.500  -0.4080   0.03933   0.03083  -0.0360   1.0000   0.1629
  -4.250  -0.3772   0.03552   0.02632  -0.0362   1.0000   0.1336
  -4.000  -0.3486   0.03236   0.02242  -0.0356   1.0000   0.1183
  -3.750  -0.3198   0.03008   0.01936  -0.0347   1.0000   0.1107
  -3.500  -0.2956   0.02750   0.01665  -0.0339   1.0000   0.1166
  -3.250  -0.2691   0.02545   0.01424  -0.0328   1.0000   0.1172
  -3.000  -0.2428   0.02360   0.01214  -0.0313   1.0000   0.1177
  -2.750  -0.2177   0.02205   0.01042  -0.0294   1.0000   0.1217
  -2.500  -0.1941   0.02062   0.00891  -0.0277   1.0000   0.1300
  -2.250  -0.1720   0.01928   0.00765  -0.0265   1.0000   0.1590
  -2.000  -0.1226   0.01476   0.00614  -0.0245   1.0000   1.0000
  -1.750  -0.1088   0.01465   0.00548  -0.0222   1.0000   1.0000
  -1.500  -0.0931   0.01458   0.00502  -0.0205   1.0000   1.0000
  -1.250  -0.0754   0.01456   0.00467  -0.0192   1.0000   1.0000
  -1.000  -0.0562   0.01456   0.00440  -0.0181   1.0000   1.0000
  -0.750  -0.0361   0.01461   0.00421  -0.0173   1.0000   1.0000
  -0.500  -0.0155   0.01468   0.00408  -0.0165   1.0000   1.0000
  -0.250   0.0055   0.01478   0.00397  -0.0159   1.0000   1.0000
   0.000   0.0267   0.01491   0.00396  -0.0153   1.0000   1.0000
   0.250   0.0480   0.01506   0.00401  -0.0147   1.0000   1.0000
   0.500   0.0693   0.01525   0.00411  -0.0142   1.0000   1.0000
   0.750   0.0906   0.01546   0.00428  -0.0137   1.0000   1.0000
   1.000   0.1118   0.01571   0.00450  -0.0133   1.0000   1.0000
   1.250   0.1329   0.01598   0.00481  -0.0129   1.0000   1.0000
   1.500   0.1538   0.01629   0.00514  -0.0125   1.0000   1.0000
   1.750   0.1746   0.01663   0.00552  -0.0121   1.0000   1.0000
   2.000   0.1952   0.01700   0.00597  -0.0118   1.0000   1.0000
   2.250   0.2156   0.01741   0.00649  -0.0115   1.0000   1.0000
   2.500   0.2358   0.01787   0.00708  -0.0113   1.0000   1.0000
   2.750   0.2557   0.01836   0.00774  -0.0110   1.0000   1.0000
   3.000   0.2754   0.01891   0.00857  -0.0108   1.0000   1.0000
   3.250   0.2948   0.01951   0.00940  -0.0107   1.0000   1.0000
   3.500   0.3138   0.02016   0.01032  -0.0105   1.0000   1.0000
   3.750   0.3325   0.02088   0.01135  -0.0105   1.0000   1.0000
   4.000   0.5350   0.02411   0.01225  -0.0217   0.1248   1.0000
   4.250   0.5681   0.02637   0.01448  -0.0212   0.1144   1.0000
   4.500   0.5981   0.02855   0.01680  -0.0207   0.1022   1.0000
   4.750   0.6290   0.03142   0.01994  -0.0200   0.1014   1.0000
   5.000   0.6586   0.03404   0.02329  -0.0188   0.1049   1.0000
   5.250   0.6861   0.03756   0.02734  -0.0177   0.1109   1.0000
   5.500   0.7126   0.04113   0.03170  -0.0164   0.1223   1.0000
   5.750   0.7379   0.04556   0.03671  -0.0156   0.1385   1.0000
   6.000   0.7628   0.05038   0.04266  -0.0155   0.1744   1.0000
   6.250   0.7852   0.06263   0.05665  -0.0321   0.3412   1.0000
   6.500   0.7374   0.07325   0.06735  -0.0528   0.4363   1.0000
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