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WACO COOTIE AIRFOIL (cootie-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: WACO COOTIE AIRFOIL (cootie-il)
Reynolds number: 100,000
Max Cl/Cd: 60.06 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cootie-il-100000.txt
Download as CSV file: xf-cootie-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WACO COOTIE AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3200   0.10700   0.10253  -0.0300   1.0000   0.0675
  -8.250  -0.3398   0.10727   0.10291  -0.0276   1.0000   0.0677
  -8.000  -0.3547   0.10727   0.10300  -0.0279   1.0000   0.0679
  -7.750  -0.3635   0.10684   0.10262  -0.0300   1.0000   0.0681
  -7.500  -0.3625   0.10106   0.09691  -0.0250   1.0000   0.0689
  -7.250  -0.3595   0.09689   0.09278  -0.0200   1.0000   0.0702
  -7.000  -0.3618   0.09456   0.09050  -0.0179   1.0000   0.0714
  -6.750  -0.3648   0.09252   0.08850  -0.0168   1.0000   0.0729
  -6.500  -0.3671   0.09050   0.08653  -0.0165   1.0000   0.0746
  -6.250  -0.3676   0.08845   0.08451  -0.0171   1.0000   0.0766
  -6.000  -0.3068   0.08375   0.07957  -0.0399   0.9906   0.0818
  -5.750  -0.2941   0.07853   0.07443  -0.0368   0.9861   0.0841
  -5.500  -0.2628   0.07444   0.07027  -0.0419   0.9795   0.0887
  -5.250  -0.1964   0.06983   0.06529  -0.0606   0.9713   0.0958
  -5.000  -0.1795   0.06538   0.06092  -0.0602   0.9641   0.0978
  -4.750  -0.1418   0.06163   0.05707  -0.0655   0.9581   0.1045
  -4.500  -0.0978   0.05759   0.05279  -0.0740   0.9495   0.1114
  -4.250  -0.0598   0.05404   0.04915  -0.0785   0.9438   0.1174
  -4.000  -0.0160   0.05058   0.04540  -0.0854   0.9354   0.1255
  -3.750   0.0333   0.04759   0.04209  -0.0922   0.9296   0.1384
  -3.250   0.1055   0.04194   0.03626  -0.0988   0.9157   0.1611
  -3.000   0.1566   0.03901   0.03308  -0.1050   0.9125   0.1836
  -2.750   0.1845   0.03720   0.03121  -0.1061   0.9022   0.2021
  -2.500   0.2281   0.03498   0.02894  -0.1100   0.8986   0.2483
  -1.750   0.3750   0.02755   0.01930  -0.1188   0.8770   0.1061
  -1.500   0.4155   0.02589   0.01732  -0.1204   0.8701   0.1041
  -1.250   0.4480   0.02500   0.01611  -0.1205   0.8599   0.1077
  -1.000   0.4865   0.02357   0.01456  -0.1217   0.8533   0.1134
  -0.750   0.5140   0.02285   0.01373  -0.1211   0.8419   0.1189
  -0.500   0.5449   0.02190   0.01274  -0.1209   0.8334   0.1300
  -0.250   0.5744   0.02079   0.01172  -0.1206   0.8247   0.1622
   0.000   0.5996   0.02018   0.01123  -0.1198   0.8142   0.2056
   0.250   0.6313   0.01950   0.01067  -0.1198   0.8075   0.2490
   0.500   0.6550   0.01866   0.01075  -0.1193   0.7960   0.5077
   0.750   0.6815   0.01787   0.01055  -0.1179   0.7859   1.0000
   1.000   0.7117   0.01772   0.01016  -0.1174   0.7781   1.0000
   1.250   0.7366   0.01787   0.01018  -0.1166   0.7662   1.0000
   1.500   0.7627   0.01796   0.01015  -0.1159   0.7552   1.0000
   1.750   0.7911   0.01787   0.00994  -0.1153   0.7461   1.0000
   2.000   0.8179   0.01788   0.00985  -0.1147   0.7351   1.0000
   2.250   0.8436   0.01798   0.00989  -0.1140   0.7229   1.0000
   2.500   0.8700   0.01804   0.00989  -0.1134   0.7113   1.0000
   2.750   0.8973   0.01806   0.00985  -0.1128   0.7001   1.0000
   3.000   0.9257   0.01800   0.00970  -0.1124   0.6892   1.0000
   3.250   0.9519   0.01813   0.00979  -0.1117   0.6760   1.0000
   3.500   0.9779   0.01832   0.00997  -0.1112   0.6625   1.0000
   3.750   1.0039   0.01854   0.01017  -0.1106   0.6488   1.0000
   4.000   1.0299   0.01880   0.01040  -0.1100   0.6349   1.0000
   4.250   1.0557   0.01912   0.01070  -0.1095   0.6209   1.0000
   4.500   1.0813   0.01948   0.01109  -0.1090   0.6069   1.0000
   4.750   1.1066   0.01987   0.01147  -0.1084   0.5929   1.0000
   5.000   1.1318   0.02023   0.01185  -0.1078   0.5786   1.0000
   5.250   1.1566   0.02057   0.01220  -0.1072   0.5640   1.0000
   5.500   1.1811   0.02086   0.01254  -0.1064   0.5491   1.0000
   5.750   1.2053   0.02113   0.01284  -0.1056   0.5343   1.0000
   6.000   1.2294   0.02141   0.01316  -0.1049   0.5199   1.0000
   6.250   1.2534   0.02168   0.01351  -0.1041   0.5057   1.0000
   6.500   1.2767   0.02194   0.01382  -0.1032   0.4909   1.0000
   6.750   1.2987   0.02207   0.01401  -0.1020   0.4734   1.0000
   7.000   1.3200   0.02207   0.01396  -0.1006   0.4530   1.0000
   7.250   1.3390   0.02231   0.01429  -0.0990   0.4328   1.0000
   7.500   1.3580   0.02261   0.01468  -0.0975   0.4131   1.0000
   7.750   1.3761   0.02295   0.01502  -0.0958   0.3926   1.0000
   8.000   1.3921   0.02341   0.01562  -0.0939   0.3708   1.0000
   8.250   1.4065   0.02394   0.01617  -0.0918   0.3472   1.0000
   8.500   1.4169   0.02460   0.01685  -0.0891   0.3176   1.0000
   8.750   1.4236   0.02545   0.01775  -0.0860   0.2797   1.0000
   9.000   1.4243   0.02672   0.01887  -0.0822   0.2218   1.0000
   9.250   1.4087   0.02911   0.02067  -0.0766   0.1506   1.0000
   9.500   1.3906   0.03229   0.02335  -0.0716   0.0993   1.0000
   9.750   1.3760   0.03551   0.02639  -0.0675   0.0785   1.0000
  10.000   1.3661   0.03852   0.02941  -0.0644   0.0677   1.0000
  10.250   1.3583   0.04150   0.03242  -0.0620   0.0611   1.0000
  10.500   1.3553   0.04420   0.03525  -0.0600   0.0562   1.0000
  10.750   1.3524   0.04698   0.03813  -0.0583   0.0529   1.0000
  11.000   1.3480   0.04999   0.04118  -0.0567   0.0505   1.0000
  11.250   1.3467   0.05275   0.04399  -0.0550   0.0487   1.0000
  11.500   1.3519   0.05499   0.04637  -0.0533   0.0468   1.0000
  11.750   1.3599   0.05703   0.04849  -0.0516   0.0449   1.0000
  12.000   1.3681   0.05910   0.05061  -0.0502   0.0429   1.0000
  12.250   1.3783   0.06114   0.05261  -0.0487   0.0408   1.0000
  12.500   1.3963   0.06313   0.05468  -0.0469   0.0392   1.0000
  12.750   1.4125   0.06552   0.05731  -0.0454   0.0385   1.0000
  13.000   1.4244   0.06850   0.06056  -0.0440   0.0382   1.0000
  13.250   1.4289   0.07208   0.06447  -0.0429   0.0380   1.0000
  13.500   1.4264   0.07615   0.06884  -0.0419   0.0380   1.0000
  13.750   1.4188   0.08060   0.07360  -0.0414   0.0381   1.0000
  14.000   1.4075   0.08539   0.07868  -0.0412   0.0383   1.0000
  14.250   1.3936   0.09054   0.08411  -0.0415   0.0385   1.0000
  14.500   1.3774   0.09603   0.08986  -0.0424   0.0387   1.0000
  14.750   1.3599   0.10186   0.09593  -0.0438   0.0389   1.0000
  15.000   1.3415   0.10808   0.10237  -0.0459   0.0392   1.0000
  15.250   1.3229   0.11468   0.10918  -0.0486   0.0394   1.0000
  15.500   1.3047   0.12167   0.11635  -0.0518   0.0397   1.0000
  15.750   1.2882   0.12892   0.12379  -0.0552   0.0400   1.0000
  16.000   1.2644   0.13733   0.13244  -0.0614   0.0404   1.0000
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