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NACA 65-206 (naca65206-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 65-206 (naca65206-il)
Reynolds number: 200,000
Max Cl/Cd: 54.16 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca65206-il-200000.txt
Download as CSV file: xf-naca65206-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5406   0.08529   0.08182  -0.0136   1.0000   0.0236
  -7.750  -0.5417   0.08158   0.07815  -0.0159   1.0000   0.0240
  -7.500  -0.5416   0.07738   0.07399  -0.0198   1.0000   0.0245
  -7.250  -0.5376   0.07287   0.06947  -0.0239   1.0000   0.0252
  -7.000  -0.5316   0.06842   0.06498  -0.0273   1.0000   0.0258
  -6.750  -0.5234   0.06405   0.06053  -0.0303   1.0000   0.0272
  -6.500  -0.5086   0.05993   0.05622  -0.0336   1.0000   0.0304
  -6.250  -0.4876   0.05824   0.05408  -0.0354   1.0000   0.0320
  -6.000  -0.4833   0.05079   0.04653  -0.0367   1.0000   0.0332
  -5.750  -0.4726   0.04677   0.04255  -0.0366   1.0000   0.0348
  -5.500  -0.4581   0.04359   0.03927  -0.0365   1.0000   0.0370
  -5.250  -0.4408   0.04049   0.03596  -0.0363   1.0000   0.0399
  -5.000  -0.4136   0.04082   0.03556  -0.0350   1.0000   0.0451
  -4.750  -0.4020   0.03409   0.02883  -0.0354   1.0000   0.0475
  -4.500  -0.3842   0.03150   0.02619  -0.0349   1.0000   0.0511
  -4.250  -0.3630   0.02930   0.02351  -0.0340   1.0000   0.0604
  -4.000  -0.3438   0.02701   0.02111  -0.0333   1.0000   0.0670
  -3.750  -0.3237   0.02496   0.01885  -0.0325   1.0000   0.0798
  -3.000  -0.2441   0.01766   0.01021  -0.0274   1.0000   0.0423
  -2.750  -0.2195   0.01576   0.00808  -0.0262   1.0000   0.0390
  -2.500  -0.1955   0.01441   0.00660  -0.0251   1.0000   0.0385
  -2.250  -0.1722   0.01338   0.00553  -0.0241   1.0000   0.0411
  -2.000  -0.1491   0.01253   0.00465  -0.0234   1.0000   0.0480
  -1.750  -0.1253   0.01184   0.00391  -0.0229   1.0000   0.0521
  -1.500  -0.1013   0.01133   0.00331  -0.0224   1.0000   0.0625
  -1.250  -0.0905   0.00833   0.00331  -0.0192   1.0000   0.8133
  -1.000  -0.0701   0.00809   0.00328  -0.0163   1.0000   1.0000
  -0.750  -0.0366   0.00822   0.00323  -0.0182   0.9970   1.0000
  -0.500   0.0045   0.00838   0.00324  -0.0216   0.9914   1.0000
  -0.250   0.0452   0.00853   0.00326  -0.0248   0.9854   1.0000
   0.000   0.0871   0.00868   0.00334  -0.0282   0.9802   1.0000
   0.250   0.1255   0.00877   0.00339  -0.0308   0.9732   1.0000
   0.500   0.1689   0.00888   0.00349  -0.0345   0.9687   1.0000
   0.750   0.2056   0.00895   0.00358  -0.0366   0.9607   1.0000
   1.000   0.2496   0.00899   0.00367  -0.0403   0.9560   1.0000
   1.250   0.2875   0.00903   0.00377  -0.0426   0.9483   1.0000
   1.500   0.3306   0.00901   0.00386  -0.0458   0.9428   1.0000
   1.750   0.3740   0.00866   0.00363  -0.0480   0.9252   1.0000
   2.000   0.4033   0.00818   0.00327  -0.0463   0.8904   1.0000
   2.250   0.4205   0.00787   0.00283  -0.0419   0.8240   1.0000
   2.500   0.4365   0.00806   0.00256  -0.0377   0.6917   1.0000
   2.750   0.4347   0.01172   0.00328  -0.0327   0.0713   1.0000
   3.000   0.4586   0.01261   0.00415  -0.0320   0.0506   1.0000
   3.250   0.4823   0.01355   0.00517  -0.0312   0.0436   1.0000
   3.500   0.5060   0.01464   0.00633  -0.0304   0.0397   1.0000
   3.750   0.5300   0.01611   0.00779  -0.0295   0.0379   1.0000
   4.000   0.5557   0.01804   0.00977  -0.0288   0.0369   1.0000
   4.250   0.5824   0.01967   0.01165  -0.0281   0.0332   1.0000
   4.500   0.6096   0.02221   0.01447  -0.0272   0.0338   1.0000
   5.250   0.6717   0.01904   0.01343  -0.0196   0.0704   1.0000
   5.500   0.6895   0.02148   0.01607  -0.0191   0.0532   1.0000
   6.500   0.7786   0.05047   0.04545  -0.0190   0.0364   1.0000
   6.750   0.7832   0.05721   0.05256  -0.0184   0.0355   1.0000
   7.000   0.7996   0.05791   0.05389  -0.0167   0.0330   1.0000
   7.250   0.8084   0.06211   0.05836  -0.0165   0.0310   1.0000
   7.500   0.8132   0.06655   0.06300  -0.0167   0.0298   1.0000
   7.750   0.8148   0.07103   0.06764  -0.0173   0.0290   1.0000
   8.000   0.8132   0.07558   0.07230  -0.0183   0.0284   1.0000
   8.250   0.8077   0.08018   0.07698  -0.0197   0.0280   1.0000
   8.500   0.7969   0.08461   0.08146  -0.0215   0.0280   1.0000
   8.750   0.7860   0.09028   0.08714  -0.0264   0.0280   1.0000
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