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RUTAN CANARD AIRFOIL (amsoil1-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: RUTAN CANARD AIRFOIL (amsoil1-il)
Reynolds number: 200,000
Max Cl/Cd: 67.46 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-amsoil1-il-200000.txt
Download as CSV file: xf-amsoil1-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RUTAN CANARD AIRFOIL                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5047   0.08354   0.07987  -0.0451   1.0000   0.0783
  -8.750  -0.5585   0.07745   0.07356  -0.0509   1.0000   0.0788
  -8.500  -0.5601   0.07360   0.06984  -0.0483   1.0000   0.0794
  -8.250  -0.5657   0.07211   0.06843  -0.0441   1.0000   0.0798
  -8.000  -0.5601   0.07020   0.06657  -0.0423   0.9987   0.0805
  -7.750  -0.5363   0.06713   0.06349  -0.0447   0.9949   0.0820
  -7.500  -0.5170   0.06289   0.05913  -0.0491   0.9894   0.0849
  -7.250  -0.5064   0.05499   0.05071  -0.0570   0.9827   0.0912
  -7.000  -0.5045   0.04038   0.03491  -0.0604   0.9744   0.0703
  -6.750  -0.4731   0.03636   0.03071  -0.0629   0.9720   0.0665
  -6.500  -0.4505   0.03195   0.02576  -0.0638   0.9658   0.0657
  -6.250  -0.4214   0.02863   0.02195  -0.0651   0.9615   0.0659
  -6.000  -0.3887   0.02598   0.01886  -0.0667   0.9584   0.0666
  -5.750  -0.3618   0.02437   0.01688  -0.0667   0.9520   0.0683
  -5.500  -0.3310   0.02279   0.01496  -0.0675   0.9472   0.0701
  -5.250  -0.2986   0.02156   0.01372  -0.0686   0.9436   0.0719
  -5.000  -0.2726   0.02083   0.01293  -0.0684   0.9369   0.0739
  -4.750  -0.2434   0.02012   0.01209  -0.0685   0.9316   0.0769
  -4.500  -0.2138   0.01924   0.01105  -0.0687   0.9275   0.0797
  -4.250  -0.1891   0.01856   0.01044  -0.0682   0.9203   0.0824
  -4.000  -0.1618   0.01807   0.00992  -0.0679   0.9149   0.0862
  -3.750  -0.1343   0.01752   0.00928  -0.0675   0.9107   0.0906
  -3.500  -0.1096   0.01702   0.00889  -0.0671   0.9036   0.0954
  -3.250  -0.0829   0.01669   0.00850  -0.0667   0.8982   0.1012
  -3.000  -0.0574   0.01613   0.00804  -0.0660   0.8940   0.1086
  -2.750  -0.0318   0.01582   0.00774  -0.0657   0.8873   0.1171
  -2.500  -0.0060   0.01547   0.00747  -0.0653   0.8818   0.1276
  -2.250   0.0199   0.01509   0.00716  -0.0647   0.8776   0.1405
  -2.000   0.0457   0.01479   0.00697  -0.0644   0.8722   0.1570
  -1.750   0.0716   0.01449   0.00677  -0.0642   0.8660   0.1815
  -1.500   0.0967   0.01388   0.00650  -0.0637   0.8614   0.2397
  -1.250   0.1080   0.01208   0.00668  -0.0604   0.8574   0.7300
  -1.000   0.1270   0.01222   0.00705  -0.0577   0.8504   0.8142
  -0.750   0.1472   0.01234   0.00720  -0.0550   0.8450   0.8561
  -0.500   0.1670   0.01242   0.00729  -0.0520   0.8410   0.8848
  -0.250   0.1872   0.01261   0.00748  -0.0498   0.8348   0.9101
   0.000   0.2107   0.01270   0.00757  -0.0480   0.8291   0.9312
   0.250   0.2422   0.01274   0.00757  -0.0478   0.8251   0.9503
   0.500   0.2842   0.01279   0.00757  -0.0500   0.8223   0.9661
   0.750   0.3382   0.01295   0.00772  -0.0552   0.8177   0.9780
   1.000   0.3996   0.01300   0.00777  -0.0619   0.8135   0.9905
   1.250   0.4516   0.01274   0.00746  -0.0663   0.8069   1.0000
   1.500   0.4712   0.01249   0.00718  -0.0645   0.7947   1.0000
   1.750   0.4911   0.01213   0.00673  -0.0624   0.7844   1.0000
   2.000   0.5117   0.01194   0.00654  -0.0609   0.7727   1.0000
   2.250   0.5324   0.01176   0.00632  -0.0593   0.7618   1.0000
   2.500   0.5535   0.01149   0.00597  -0.0576   0.7508   1.0000
   2.750   0.5739   0.01132   0.00580  -0.0559   0.7367   1.0000
   3.000   0.5950   0.01119   0.00566  -0.0544   0.7237   1.0000
   3.250   0.6171   0.01106   0.00549  -0.0530   0.7112   1.0000
   3.500   0.6402   0.01094   0.00533  -0.0517   0.6971   1.0000
   3.750   0.6639   0.01086   0.00525  -0.0507   0.6788   1.0000
   4.000   0.6883   0.01081   0.00519  -0.0497   0.6548   1.0000
   4.250   0.7128   0.01080   0.00509  -0.0487   0.6228   1.0000
   4.500   0.7360   0.01091   0.00502  -0.0474   0.5670   1.0000
   4.750   0.7495   0.01187   0.00513  -0.0447   0.4086   1.0000
   5.000   0.7546   0.01398   0.00612  -0.0418   0.2259   1.0000
   5.250   0.7713   0.01511   0.00687  -0.0404   0.1759   1.0000
   5.500   0.7912   0.01594   0.00753  -0.0393   0.1521   1.0000
   5.750   0.8117   0.01670   0.00818  -0.0383   0.1365   1.0000
   6.000   0.8318   0.01750   0.00886  -0.0373   0.1249   1.0000
   6.250   0.8529   0.01819   0.00949  -0.0364   0.1154   1.0000
   6.500   0.8740   0.01893   0.01021  -0.0354   0.1077   1.0000
   6.750   0.8941   0.01980   0.01097  -0.0344   0.1013   1.0000
   7.000   0.9162   0.02052   0.01173  -0.0335   0.0959   1.0000
   7.250   0.9378   0.02126   0.01240  -0.0327   0.0911   1.0000
   7.500   0.9598   0.02227   0.01337  -0.0320   0.0871   1.0000
   7.750   0.9828   0.02301   0.01417  -0.0313   0.0835   1.0000
   8.000   1.0057   0.02383   0.01493  -0.0307   0.0803   1.0000
   8.250   1.0301   0.02502   0.01609  -0.0304   0.0773   1.0000
   8.500   1.0536   0.02586   0.01705  -0.0298   0.0747   1.0000
   8.750   1.0772   0.02678   0.01800  -0.0293   0.0724   1.0000
   9.000   1.1017   0.02782   0.01897  -0.0290   0.0702   1.0000
   9.250   1.1267   0.02926   0.02048  -0.0289   0.0681   1.0000
   9.500   1.1487   0.03037   0.02178  -0.0281   0.0662   1.0000
   9.750   1.1713   0.03158   0.02311  -0.0275   0.0645   1.0000
  10.000   1.1930   0.03271   0.02428  -0.0269   0.0629   1.0000
  10.250   1.2179   0.03429   0.02580  -0.0270   0.0612   1.0000
  10.500   1.2352   0.03607   0.02786  -0.0258   0.0599   1.0000
  10.750   1.2503   0.03787   0.02997  -0.0243   0.0587   1.0000
  11.000   1.2645   0.03975   0.03211  -0.0229   0.0575   1.0000
  11.250   1.2789   0.04140   0.03393  -0.0215   0.0562   1.0000
  11.500   1.2968   0.04268   0.03522  -0.0207   0.0550   1.0000
  11.750   1.3147   0.04448   0.03701  -0.0202   0.0539   1.0000
  12.000   1.3202   0.04756   0.04038  -0.0183   0.0532   1.0000
  12.250   1.3143   0.05030   0.04352  -0.0149   0.0527   1.0000
  12.500   1.3014   0.05316   0.04674  -0.0109   0.0524   1.0000
  12.750   1.2846   0.05640   0.05031  -0.0073   0.0521   1.0000
  13.000   1.2646   0.06011   0.05433  -0.0044   0.0519   1.0000
  13.250   1.2412   0.06434   0.05886  -0.0022   0.0517   1.0000
  13.500   1.2146   0.06923   0.06402  -0.0010   0.0517   1.0000
  13.750   1.1850   0.07486   0.06991  -0.0008   0.0519   1.0000
  14.000   1.1530   0.08137   0.07666  -0.0019   0.0521   1.0000
  14.250   1.1195   0.08883   0.08432  -0.0044   0.0524   1.0000
  14.500   1.0864   0.09718   0.09284  -0.0082   0.0528   1.0000
  14.750   1.0576   0.10597   0.10175  -0.0127   0.0532   1.0000
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