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NACA 63-206 (naca63206-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-206 (naca63206-il)
Reynolds number: 200,000
Max Cl/Cd: 57.03 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca63206-il-200000.txt
Download as CSV file: xf-naca63206-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4796   0.09868   0.09536  -0.0054   1.0000   0.0283
  -9.000  -0.4798   0.09466   0.09137  -0.0080   1.0000   0.0286
  -7.000  -0.5405   0.06502   0.06148  -0.0303   1.0000   0.0300
  -6.750  -0.5334   0.06243   0.05898  -0.0287   1.0000   0.0326
  -6.500  -0.5224   0.05827   0.05473  -0.0309   1.0000   0.0345
  -6.250  -0.5087   0.05394   0.05019  -0.0332   1.0000   0.0365
  -6.000  -0.4899   0.04982   0.04577  -0.0354   1.0000   0.0397
  -5.750  -0.4650   0.04890   0.04416  -0.0363   1.0000   0.0416
  -5.500  -0.4343   0.02717   0.02301  -0.0366   1.0000   0.0447
  -5.250  -0.4170   0.02404   0.01974  -0.0369   1.0000   0.0481
  -5.000  -0.3948   0.02089   0.01592  -0.0375   1.0000   0.0559
  -4.750  -0.3942   0.03182   0.02651  -0.0382   1.0000   0.0585
  -4.500  -0.3710   0.02965   0.02391  -0.0381   1.0000   0.0697
  -4.250  -0.3490   0.02720   0.02142  -0.0378   1.0000   0.0772
  -3.500  -0.2639   0.01819   0.01087  -0.0337   1.0000   0.0393
  -3.250  -0.2387   0.01609   0.00849  -0.0327   1.0000   0.0372
  -3.000  -0.2141   0.01460   0.00686  -0.0316   1.0000   0.0371
  -2.500  -0.1664   0.01235   0.00454  -0.0300   1.0000   0.0456
  -2.250  -0.1421   0.01156   0.00375  -0.0294   1.0000   0.0510
  -2.000  -0.1172   0.01082   0.00295  -0.0289   1.0000   0.0656
  -1.750  -0.0994   0.00784   0.00269  -0.0277   1.0000   0.7376
  -1.500  -0.0884   0.00768   0.00279  -0.0235   1.0000   0.8378
  -1.250  -0.0778   0.00751   0.00283  -0.0186   1.0000   0.9570
  -1.000  -0.0436   0.00747   0.00264  -0.0206   1.0000   1.0000
  -0.750  -0.0194   0.00757   0.00261  -0.0207   1.0000   1.0000
  -0.500   0.0067   0.00770   0.00263  -0.0212   0.9991   1.0000
  -0.250   0.0511   0.00786   0.00268  -0.0251   0.9917   1.0000
   0.000   0.0951   0.00798   0.00274  -0.0289   0.9841   1.0000
   0.250   0.1376   0.00807   0.00280  -0.0323   0.9759   1.0000
   0.500   0.1830   0.00813   0.00286  -0.0362   0.9692   1.0000
   0.750   0.2246   0.00815   0.00291  -0.0392   0.9602   1.0000
   1.000   0.2691   0.00815   0.00296  -0.0428   0.9531   1.0000
   1.250   0.3090   0.00813   0.00300  -0.0453   0.9431   1.0000
   1.500   0.3456   0.00810   0.00305  -0.0469   0.9304   1.0000
   1.750   0.3790   0.00807   0.00314  -0.0476   0.9154   1.0000
   2.000   0.4052   0.00801   0.00313  -0.0464   0.8909   1.0000
   2.250   0.4245   0.00786   0.00292  -0.0429   0.8431   1.0000
   2.500   0.4438   0.00788   0.00276  -0.0397   0.7776   1.0000
   2.750   0.4642   0.00814   0.00270  -0.0372   0.6851   1.0000
   3.000   0.4766   0.00965   0.00281  -0.0339   0.3667   1.0000
   3.250   0.4913   0.01261   0.00427  -0.0325   0.0559   1.0000
   3.500   0.5154   0.01366   0.00534  -0.0319   0.0439   1.0000
   3.750   0.5403   0.01466   0.00642  -0.0312   0.0398   1.0000
   4.000   0.5650   0.01595   0.00775  -0.0304   0.0370   1.0000
   4.250   0.5907   0.01755   0.00941  -0.0296   0.0360   1.0000
   4.500   0.6156   0.02018   0.01213  -0.0291   0.0315   1.0000
   4.750   0.6425   0.02231   0.01453  -0.0283   0.0310   1.0000
   5.000   0.6694   0.02498   0.01750  -0.0275   0.0328   1.0000
   7.750   0.8355   0.07355   0.06965  -0.0211   0.0320   1.0000
   8.000   0.8364   0.07770   0.07403  -0.0214   0.0319   1.0000
   8.250   0.8339   0.08183   0.07835  -0.0221   0.0318   1.0000
   8.500   0.8281   0.08600   0.08267  -0.0232   0.0317   1.0000
   8.750   0.8177   0.09000   0.08676  -0.0243   0.0317   1.0000
   9.000   0.8071   0.09455   0.09136  -0.0271   0.0317   1.0000
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