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NACA 63-206 (naca63206-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-206 (naca63206-il)
Reynolds number: 500,000
Max Cl/Cd: 72.44 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca63206-il-500000.txt
Download as CSV file: xf-naca63206-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-206                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5410   0.08706   0.08483  -0.0090   1.0000   0.0093
  -8.000  -0.5401   0.08293   0.08073  -0.0115   1.0000   0.0093
  -7.750  -0.5451   0.07767   0.07554  -0.0155   1.0000   0.0093
  -7.500  -0.5411   0.07199   0.06984  -0.0219   1.0000   0.0094
  -7.250  -0.5442   0.06448   0.06226  -0.0272   1.0000   0.0096
  -7.000  -0.5395   0.05887   0.05656  -0.0305   1.0000   0.0099
  -6.750  -0.5314   0.05419   0.05177  -0.0327   1.0000   0.0102
  -6.500  -0.5203   0.05083   0.04833  -0.0340   1.0000   0.0108
  -6.250  -0.5060   0.04734   0.04472  -0.0352   1.0000   0.0117
  -6.000  -0.4890   0.04360   0.04082  -0.0363   1.0000   0.0130
  -5.750  -0.4690   0.03987   0.03683  -0.0369   1.0000   0.0147
  -5.500  -0.4379   0.03956   0.03626  -0.0358   1.0000   0.0172
  -3.750  -0.2880   0.01533   0.00988  -0.0328   1.0000   0.0149
  -3.500  -0.2634   0.01332   0.00761  -0.0317   1.0000   0.0151
  -3.250  -0.2399   0.01230   0.00642  -0.0307   1.0000   0.0164
  -3.000  -0.2170   0.01117   0.00519  -0.0298   1.0000   0.0185
  -2.750  -0.1878   0.00989   0.00384  -0.0302   0.9988   0.0203
  -2.500  -0.1507   0.00914   0.00303  -0.0323   0.9955   0.0239
  -2.250  -0.1140   0.00869   0.00253  -0.0343   0.9917   0.0278
  -2.000  -0.0773   0.00810   0.00186  -0.0363   0.9873   0.0388
  -1.750  -0.0430   0.00605   0.00140  -0.0392   0.9842   0.4998
  -1.500  -0.0084   0.00541   0.00142  -0.0409   0.9799   0.6910
  -1.250   0.0245   0.00517   0.00144  -0.0418   0.9730   0.7738
  -1.000   0.0558   0.00500   0.00147  -0.0421   0.9659   0.8405
  -0.750   0.0844   0.00490   0.00146  -0.0418   0.9562   0.8809
  -0.500   0.1118   0.00484   0.00142  -0.0413   0.9445   0.9035
  -0.250   0.1368   0.00479   0.00137  -0.0403   0.9316   0.9244
   0.000   0.1615   0.00474   0.00131  -0.0392   0.9183   0.9450
   0.250   0.1903   0.00469   0.00125  -0.0392   0.9054   0.9661
   0.500   0.2262   0.00466   0.00121  -0.0408   0.8928   0.9865
   0.750   0.2569   0.00468   0.00118  -0.0414   0.8770   1.0000
   1.000   0.2831   0.00475   0.00118  -0.0411   0.8594   1.0000
   1.250   0.3096   0.00482   0.00120  -0.0407   0.8397   1.0000
   1.500   0.3350   0.00492   0.00120  -0.0400   0.8091   1.0000
   1.750   0.3599   0.00508   0.00123  -0.0392   0.7661   1.0000
   2.000   0.3841   0.00534   0.00123  -0.0382   0.6959   1.0000
   2.250   0.4093   0.00565   0.00130  -0.0376   0.6302   1.0000
   2.500   0.4335   0.00615   0.00142  -0.0370   0.5267   1.0000
   2.750   0.4521   0.00793   0.00186  -0.0362   0.2031   1.0000
   3.000   0.4747   0.00942   0.00262  -0.0357   0.0311   1.0000
   3.250   0.5016   0.00986   0.00316  -0.0355   0.0262   1.0000
   3.500   0.5271   0.01068   0.00406  -0.0351   0.0218   1.0000
   3.750   0.5504   0.01216   0.00566  -0.0342   0.0201   1.0000
   4.000   0.5775   0.01249   0.00604  -0.0341   0.0185   1.0000
   4.250   0.6030   0.01350   0.00713  -0.0335   0.0170   1.0000
   4.500   0.6285   0.01493   0.00868  -0.0328   0.0157   1.0000
   4.750   0.6544   0.01721   0.01117  -0.0318   0.0160   1.0000
   5.000   0.6804   0.01851   0.01266  -0.0314   0.0144   1.0000
   5.250   0.7049   0.01965   0.01389  -0.0313   0.0124   1.0000
   5.500   0.7279   0.02327   0.01789  -0.0302   0.0118   1.0000
   5.750   0.7316   0.01737   0.01321  -0.0257   0.0154   1.0000
   6.000   0.7506   0.02070   0.01686  -0.0247   0.0144   1.0000
   6.250   0.7678   0.02430   0.02075  -0.0240   0.0137   1.0000
   6.500   0.7829   0.02809   0.02478  -0.0234   0.0131   1.0000
   6.750   0.7954   0.03205   0.02893  -0.0229   0.0126   1.0000
   7.000   0.8049   0.03666   0.03375  -0.0224   0.0122   1.0000
   7.250   0.8084   0.04227   0.03959  -0.0220   0.0119   1.0000
   7.500   0.8016   0.04973   0.04728  -0.0218   0.0115   1.0000
   7.750   0.7863   0.05766   0.05542  -0.0218   0.0113   1.0000
   8.000   0.8246   0.07159   0.06928  -0.0242   0.0111   1.0000
   8.250   0.8197   0.07619   0.07400  -0.0250   0.0111   1.0000
   8.500   0.8079   0.08030   0.07818  -0.0256   0.0111   1.0000
   8.750   0.7964   0.08525   0.08320  -0.0287   0.0111   1.0000
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