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WACO COOTIE AIRFOIL (cootie-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: WACO COOTIE AIRFOIL (cootie-il)
Reynolds number: 50,000
Max Cl/Cd: 39.75 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cootie-il-50000-n5.txt
Download as CSV file: xf-cootie-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3145   0.11368   0.10731  -0.0332   1.0000   0.0866
  -8.500  -0.3279   0.11331   0.10709  -0.0325   1.0000   0.0868
  -8.250  -0.3385   0.11267   0.10656  -0.0328   1.0000   0.0870
  -8.000  -0.3199   0.10488   0.09877  -0.0275   1.0000   0.0895
  -7.750  -0.3239   0.10271   0.09667  -0.0255   1.0000   0.0908
  -7.500  -0.3295   0.10082   0.09487  -0.0239   1.0000   0.0920
  -7.250  -0.3352   0.09898   0.09311  -0.0227   1.0000   0.0934
  -7.000  -0.3401   0.09712   0.09132  -0.0219   1.0000   0.0950
  -6.750  -0.3438   0.09520   0.08947  -0.0218   1.0000   0.0967
  -6.500  -0.3149   0.09225   0.08641  -0.0352   0.9912   0.1008
  -6.000  -0.2738   0.08281   0.07691  -0.0394   0.9787   0.1078
  -5.750  -0.2389   0.07906   0.07299  -0.0495   0.9698   0.1139
  -5.500  -0.2006   0.07467   0.06841  -0.0592   0.9622   0.1157
  -5.250  -0.1840   0.07052   0.06430  -0.0586   0.9550   0.1195
  -4.750  -0.1198   0.06316   0.05664  -0.0692   0.9398   0.1349
  -4.500  -0.0564   0.05644   0.04922  -0.0818   0.9341   0.0859
  -4.250  -0.0277   0.05300   0.04566  -0.0845   0.9258   0.0831
  -4.000   0.0178   0.04933   0.04161  -0.0907   0.9208   0.0840
  -3.750   0.0502   0.04637   0.03838  -0.0935   0.9118   0.0818
  -3.500   0.0951   0.04300   0.03457  -0.0985   0.9068   0.0791
  -3.250   0.1309   0.04040   0.03155  -0.1013   0.8985   0.0776
  -3.000   0.1734   0.03787   0.02853  -0.1049   0.8929   0.0771
  -2.750   0.2068   0.03632   0.02666  -0.1066   0.8846   0.0802
  -2.500   0.2459   0.03462   0.02449  -0.1090   0.8781   0.0834
  -2.250   0.2789   0.03317   0.02264  -0.1101   0.8696   0.0841
  -2.000   0.3167   0.03171   0.02076  -0.1118   0.8631   0.0852
  -1.750   0.3475   0.03071   0.01935  -0.1122   0.8538   0.0868
  -1.500   0.3836   0.02959   0.01807  -0.1136   0.8475   0.0896
  -1.250   0.4107   0.02899   0.01730  -0.1133   0.8372   0.0935
  -1.000   0.4478   0.02821   0.01618  -0.1144   0.8309   0.1025
  -0.750   0.4751   0.02782   0.01565  -0.1141   0.8203   0.1152
  -0.500   0.5040   0.02718   0.01496  -0.1140   0.8107   0.1309
  -0.250   0.5367   0.02641   0.01417  -0.1145   0.8028   0.1605
   0.000   0.5618   0.02598   0.01392  -0.1142   0.7912   0.2060
   0.250   0.5895   0.02552   0.01364  -0.1140   0.7806   0.2484
   0.750   0.6427   0.02370   0.01318  -0.1125   0.7600   1.0000
   1.000   0.6684   0.02389   0.01313  -0.1118   0.7486   1.0000
   1.250   0.6966   0.02396   0.01300  -0.1114   0.7387   1.0000
   1.500   0.7243   0.02404   0.01291  -0.1110   0.7286   1.0000
   1.750   0.7488   0.02429   0.01304  -0.1103   0.7169   1.0000
   2.000   0.7749   0.02446   0.01312  -0.1097   0.7061   1.0000
   2.250   0.8047   0.02442   0.01298  -0.1095   0.6973   1.0000
   2.500   0.8294   0.02467   0.01318  -0.1088   0.6854   1.0000
   2.750   0.8545   0.02492   0.01339  -0.1082   0.6740   1.0000
   3.000   0.8814   0.02508   0.01353  -0.1077   0.6634   1.0000
   3.250   0.9105   0.02510   0.01350  -0.1075   0.6537   1.0000
   3.500   0.9347   0.02546   0.01387  -0.1068   0.6414   1.0000
   3.750   0.9596   0.02579   0.01424  -0.1062   0.6295   1.0000
   4.000   0.9857   0.02606   0.01453  -0.1057   0.6181   1.0000
   4.250   1.0142   0.02622   0.01468  -0.1054   0.6078   1.0000
   4.500   1.0374   0.02671   0.01527  -0.1046   0.5951   1.0000
   4.750   1.0605   0.02722   0.01586  -0.1039   0.5826   1.0000
   5.000   1.0843   0.02771   0.01644  -0.1032   0.5706   1.0000
   5.250   1.1095   0.02812   0.01696  -0.1027   0.5595   1.0000
   5.500   1.1344   0.02855   0.01749  -0.1021   0.5482   1.0000
   5.750   1.1553   0.02924   0.01834  -0.1012   0.5359   1.0000
   6.000   1.1770   0.02989   0.01914  -0.1004   0.5242   1.0000
   6.250   1.2005   0.03042   0.01984  -0.0997   0.5133   1.0000
   6.500   1.2254   0.03083   0.02038  -0.0990   0.5027   1.0000
   6.750   1.2448   0.03150   0.02123  -0.0978   0.4897   1.0000
   7.000   1.2644   0.03208   0.02198  -0.0965   0.4763   1.0000
   7.250   1.2838   0.03259   0.02266  -0.0951   0.4624   1.0000
   7.500   1.3026   0.03308   0.02335  -0.0936   0.4479   1.0000
   7.750   1.3204   0.03354   0.02398  -0.0919   0.4325   1.0000
   8.000   1.3362   0.03375   0.02423  -0.0897   0.4125   1.0000
   8.250   1.3439   0.03444   0.02505  -0.0867   0.3905   1.0000
   8.500   1.3522   0.03500   0.02560  -0.0837   0.3675   1.0000
   8.750   1.3541   0.03603   0.02670  -0.0803   0.3432   1.0000
   9.000   1.3531   0.03718   0.02792  -0.0766   0.3195   1.0000
   9.250   1.3545   0.03859   0.02946  -0.0737   0.2992   1.0000
   9.500   1.3563   0.04015   0.03116  -0.0711   0.2798   1.0000
   9.750   1.3537   0.04219   0.03335  -0.0687   0.2542   1.0000
  10.000   1.3466   0.04473   0.03587  -0.0664   0.2173   1.0000
  10.250   1.3352   0.04793   0.03879  -0.0644   0.1757   1.0000
  10.500   1.3208   0.05187   0.04242  -0.0628   0.1391   1.0000
  10.750   1.3072   0.05613   0.04650  -0.0618   0.1104   1.0000
  11.000   1.2941   0.06063   0.05091  -0.0612   0.0935   1.0000
  11.250   1.2813   0.06534   0.05561  -0.0610   0.0819   1.0000
  11.500   1.2679   0.07030   0.06058  -0.0610   0.0730   1.0000
  11.750   1.2584   0.07492   0.06535  -0.0611   0.0640   1.0000
  12.000   1.2470   0.07988   0.07035  -0.0616   0.0585   1.0000
  12.250   1.2394   0.08443   0.07505  -0.0619   0.0529   1.0000
  12.500   1.2310   0.08919   0.07988  -0.0626   0.0492   1.0000
  12.750   1.2244   0.09373   0.08448  -0.0632   0.0461   1.0000
  13.000   1.2201   0.09797   0.08886  -0.0638   0.0431   1.0000
  13.250   1.2160   0.10222   0.09325  -0.0645   0.0408   1.0000
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