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Coanda 3 (coanda3-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: Coanda 3 (coanda3-il)
Reynolds number: 200,000
Max Cl/Cd: 75.5 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-coanda3-il-200000.txt
Download as CSV file: xf-coanda3-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Coanda 3                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4367   0.10395   0.10054  -0.0284   1.0000   0.0490
  -9.250  -0.4439   0.10164   0.09829  -0.0301   1.0000   0.0492
  -9.000  -0.4551   0.09937   0.09610  -0.0310   1.0000   0.0493
  -8.750  -0.4269   0.09281   0.08945  -0.0250   1.0000   0.0519
  -8.500  -0.4263   0.09034   0.08702  -0.0240   1.0000   0.0536
  -7.250  -0.4686   0.07905   0.07580  -0.0293   1.0000   0.0607
  -7.000  -0.4717   0.07348   0.07031  -0.0273   1.0000   0.0615
  -6.750  -0.4687   0.07041   0.06728  -0.0242   1.0000   0.0623
  -6.500  -0.4654   0.06726   0.06413  -0.0228   1.0000   0.0629
  -6.250  -0.4606   0.06422   0.06106  -0.0218   1.0000   0.0637
  -6.000  -0.4547   0.06085   0.05764  -0.0212   1.0000   0.0644
  -5.750  -0.4470   0.05727   0.05397  -0.0210   1.0000   0.0649
  -5.500  -0.4376   0.05361   0.05021  -0.0207   1.0000   0.0652
  -5.250  -0.4304   0.03910   0.03492  -0.0219   1.0000   0.0377
  -5.000  -0.4254   0.02718   0.02182  -0.0189   1.0000   0.0288
  -4.750  -0.4106   0.02328   0.01732  -0.0166   1.0000   0.0273
  -4.500  -0.3921   0.02058   0.01406  -0.0145   1.0000   0.0259
  -4.250  -0.3718   0.01874   0.01179  -0.0125   1.0000   0.0254
  -4.000  -0.3512   0.01775   0.01056  -0.0109   0.9999   0.0280
  -3.750  -0.3151   0.01671   0.00925  -0.0122   0.9962   0.0282
  -3.500  -0.2790   0.01610   0.00842  -0.0136   0.9921   0.0282
  -3.250  -0.2429   0.01565   0.00776  -0.0150   0.9873   0.0293
  -3.000  -0.2042   0.01535   0.00739  -0.0170   0.9833   0.0340
  -2.750  -0.1701   0.01521   0.00744  -0.0183   0.9773   0.0693
  -2.500  -0.1279   0.01571   0.00780  -0.0212   0.9718   0.0875
  -2.250  -0.0886   0.01599   0.00801  -0.0236   0.9647   0.0960
  -2.000  -0.0451   0.01639   0.00835  -0.0270   0.9582   0.1089
  -1.750  -0.0087   0.01634   0.00827  -0.0290   0.9506   0.1186
  -1.500   0.0331   0.01610   0.00798  -0.0318   0.9451   0.1246
  -1.250   0.0680   0.01592   0.00783  -0.0334   0.9376   0.1378
  -1.000   0.1091   0.01542   0.00732  -0.0360   0.9322   0.1427
  -0.750   0.1461   0.01488   0.00687  -0.0378   0.9255   0.1472
  -0.500   0.1867   0.01436   0.00638  -0.0402   0.9190   0.1526
  -0.250   0.2269   0.01376   0.00588  -0.0425   0.9133   0.1592
   0.000   0.2630   0.01332   0.00550  -0.0439   0.9062   0.1683
   0.250   0.3075   0.01272   0.00507  -0.0472   0.9029   0.1868
   0.500   0.3274   0.01121   0.00487  -0.0456   0.8922   0.5549
   0.750   0.5103   0.00999   0.00460  -0.0784   0.9019   1.0000
   1.000   0.5428   0.00976   0.00439  -0.0790   0.8868   1.0000
   1.250   0.5718   0.00960   0.00422  -0.0788   0.8687   1.0000
   1.500   0.6027   0.00944   0.00406  -0.0790   0.8489   1.0000
   1.750   0.6292   0.00933   0.00394  -0.0783   0.8233   1.0000
   2.000   0.6572   0.00924   0.00383  -0.0779   0.7908   1.0000
   2.250   0.6854   0.00923   0.00370  -0.0774   0.7502   1.0000
   2.500   0.7097   0.00940   0.00370  -0.0763   0.7055   1.0000
   2.750   0.7282   0.00975   0.00377  -0.0739   0.6410   1.0000
   3.000   0.7387   0.01035   0.00386  -0.0700   0.5340   1.0000
   3.250   0.7485   0.01109   0.00409  -0.0663   0.4402   1.0000
   3.500   0.7615   0.01180   0.00446  -0.0634   0.3799   1.0000
   3.750   0.7781   0.01234   0.00480  -0.0613   0.3394   1.0000
   4.000   0.7949   0.01287   0.00511  -0.0593   0.2917   1.0000
   4.250   0.8126   0.01338   0.00541  -0.0574   0.2379   1.0000
   4.500   0.8289   0.01408   0.00576  -0.0553   0.1731   1.0000
   4.750   0.8365   0.01577   0.00658  -0.0519   0.0415   1.0000
   5.000   0.8537   0.01661   0.00745  -0.0497   0.0296   1.0000
   5.250   0.8720   0.01736   0.00838  -0.0477   0.0268   1.0000
   5.500   0.8890   0.01821   0.00943  -0.0454   0.0257   1.0000
   5.750   0.9045   0.01914   0.01052  -0.0429   0.0253   1.0000
   6.000   0.9184   0.02018   0.01167  -0.0403   0.0252   1.0000
   6.250   0.9318   0.02143   0.01300  -0.0375   0.0252   1.0000
   6.500   0.9473   0.02271   0.01436  -0.0351   0.0245   1.0000
   6.750   0.9642   0.02403   0.01577  -0.0331   0.0225   1.0000
   7.000   0.9842   0.02579   0.01767  -0.0315   0.0231   1.0000
   7.250   1.0069   0.02810   0.02013  -0.0303   0.0240   1.0000
   7.500   1.0346   0.03250   0.02471  -0.0302   0.0261   1.0000
   7.750   1.0556   0.03232   0.02491  -0.0274   0.0298   1.0000
   8.000   1.0805   0.03663   0.02996  -0.0246   0.0421   1.0000
  13.500   0.6752   0.14811   0.14484  -0.0190   0.0704   1.0000
  13.750   0.6450   0.15186   0.14855  -0.0256   0.0687   1.0000
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