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WACO COOTIE AIRFOIL (cootie-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: WACO COOTIE AIRFOIL (cootie-il)
Reynolds number: 1,000,000
Max Cl/Cd: 136.88 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cootie-il-1000000.txt
Download as CSV file: xf-cootie-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2597   0.08848   0.08678  -0.0431   0.9267   0.0144
  -8.500  -0.2522   0.08603   0.08429  -0.0442   0.9137   0.0147
  -8.250  -0.2446   0.08336   0.08158  -0.0457   0.9031   0.0151
  -8.000  -0.2370   0.08052   0.07870  -0.0479   0.8942   0.0158
  -7.750  -0.2204   0.07510   0.07323  -0.0574   0.8850   0.0173
  -7.500  -0.2031   0.07048   0.06857  -0.0634   0.8783   0.0174
  -7.250  -0.1844   0.06569   0.06373  -0.0690   0.8717   0.0174
  -6.250  -0.0714   0.03532   0.03320  -0.0813   0.8325   0.0220
  -6.000  -0.0482   0.03028   0.02806  -0.0862   0.8272   0.0221
  -5.750  -0.0282   0.02130   0.01884  -0.0932   0.8230   0.0227
  -5.500  -0.0059   0.01969   0.01718  -0.0942   0.8167   0.0232
  -5.250   0.0172   0.01840   0.01583  -0.0949   0.8101   0.0239
  -5.000   0.0423   0.01654   0.01387  -0.0964   0.8036   0.0253
  -4.750   0.0751   0.01384   0.01093  -0.0985   0.7970   0.0282
  -3.750   0.1857   0.01268   0.00777  -0.1078   0.7804   0.0292
  -3.500   0.2141   0.01196   0.00687  -0.1078   0.7684   0.0289
  -3.250   0.2422   0.01085   0.00554  -0.1080   0.7566   0.0293
  -3.000   0.2704   0.01009   0.00463  -0.1080   0.7439   0.0297
  -2.750   0.2986   0.00958   0.00400  -0.1081   0.7286   0.0301
  -2.500   0.3267   0.00920   0.00350  -0.1081   0.7112   0.0305
  -2.250   0.3547   0.00891   0.00310  -0.1081   0.6935   0.0308
  -2.000   0.3826   0.00869   0.00277  -0.1081   0.6765   0.0310
  -1.750   0.4107   0.00850   0.00248  -0.1081   0.6616   0.0312
  -1.500   0.4389   0.00834   0.00224  -0.1081   0.6489   0.0315
  -1.250   0.4671   0.00822   0.00206  -0.1082   0.6386   0.0323
  -1.000   0.4954   0.00812   0.00190  -0.1083   0.6294   0.0330
  -0.750   0.5239   0.00802   0.00175  -0.1084   0.6208   0.0337
  -0.500   0.5522   0.00796   0.00165  -0.1085   0.6128   0.0347
  -0.250   0.5806   0.00792   0.00157  -0.1087   0.6046   0.0356
   0.000   0.6090   0.00790   0.00152  -0.1088   0.5973   0.0362
   0.250   0.6375   0.00789   0.00147  -0.1089   0.5900   0.0379
   0.500   0.6658   0.00789   0.00145  -0.1090   0.5832   0.0416
   0.750   0.6942   0.00782   0.00151  -0.1092   0.5758   0.0776
   1.000   0.7223   0.00788   0.00158  -0.1093   0.5684   0.0926
   1.250   0.7506   0.00791   0.00162  -0.1095   0.5601   0.0991
   1.500   0.7787   0.00796   0.00168  -0.1096   0.5520   0.1056
   1.750   0.8066   0.00803   0.00172  -0.1097   0.5418   0.1090
   2.000   0.8346   0.00806   0.00175  -0.1098   0.5296   0.1162
   2.250   0.8624   0.00813   0.00181  -0.1099   0.5167   0.1227
   2.750   0.9119   0.00668   0.00213  -0.1093   0.4877   1.0000
   3.000   0.9390   0.00686   0.00222  -0.1093   0.4700   1.0000
   3.250   0.9659   0.00707   0.00232  -0.1093   0.4515   1.0000
   3.500   0.9928   0.00729   0.00245  -0.1093   0.4312   1.0000
   3.750   1.0189   0.00758   0.00261  -0.1092   0.4069   1.0000
   4.000   1.0448   0.00789   0.00279  -0.1090   0.3807   1.0000
   4.250   1.0708   0.00817   0.00298  -0.1089   0.3604   1.0000
   4.500   1.0970   0.00843   0.00317  -0.1088   0.3443   1.0000
   4.750   1.1230   0.00870   0.00336  -0.1087   0.3276   1.0000
   5.000   1.1486   0.00901   0.00358  -0.1085   0.3086   1.0000
   5.250   1.1742   0.00930   0.00381  -0.1084   0.2920   1.0000
   5.500   1.1996   0.00961   0.00404  -0.1082   0.2732   1.0000
   5.750   1.2235   0.01006   0.00433  -0.1078   0.2419   1.0000
   6.000   1.2407   0.01119   0.00499  -0.1064   0.1646   1.0000
   6.250   1.2546   0.01264   0.00594  -0.1046   0.0817   1.0000
   6.500   1.2754   0.01334   0.00649  -0.1036   0.0547   1.0000
   6.750   1.2923   0.01440   0.00730  -0.1021   0.0174   1.0000
   7.000   1.3144   0.01490   0.00783  -0.1013   0.0149   1.0000
   7.250   1.3366   0.01537   0.00836  -0.1006   0.0137   1.0000
   7.500   1.3584   0.01584   0.00887  -0.0998   0.0129   1.0000
   7.750   1.3792   0.01637   0.00945  -0.0989   0.0121   1.0000
   8.000   1.3985   0.01699   0.01012  -0.0977   0.0114   1.0000
   8.250   1.4144   0.01786   0.01107  -0.0960   0.0107   1.0000
   8.500   1.4286   0.01877   0.01208  -0.0940   0.0102   1.0000
   8.750   1.4459   0.01936   0.01272  -0.0925   0.0099   1.0000
   9.000   1.4611   0.01998   0.01340  -0.0907   0.0096   1.0000
   9.250   1.4731   0.02069   0.01415  -0.0884   0.0092   1.0000
   9.500   1.4843   0.02148   0.01500  -0.0861   0.0088   1.0000
   9.750   1.4941   0.02242   0.01601  -0.0837   0.0085   1.0000
  10.000   1.5029   0.02347   0.01713  -0.0814   0.0082   1.0000
  10.250   1.5090   0.02478   0.01851  -0.0790   0.0079   1.0000
  10.500   1.5099   0.02655   0.02036  -0.0762   0.0077   1.0000
  10.750   1.5018   0.02918   0.02311  -0.0728   0.0075   1.0000
  11.000   1.4992   0.03153   0.02556  -0.0704   0.0073   1.0000
  11.250   1.5081   0.03296   0.02707  -0.0691   0.0072   1.0000
  11.500   1.5139   0.03472   0.02891  -0.0678   0.0071   1.0000
  11.750   1.5185   0.03666   0.03094  -0.0664   0.0070   1.0000
  12.000   1.5217   0.03878   0.03315  -0.0652   0.0069   1.0000
  12.250   1.5233   0.04112   0.03558  -0.0640   0.0068   1.0000
  12.500   1.5247   0.04356   0.03811  -0.0629   0.0066   1.0000
  12.750   1.5252   0.04614   0.04078  -0.0619   0.0065   1.0000
  13.000   1.5256   0.04882   0.04355  -0.0612   0.0064   1.0000
  13.250   1.5259   0.05159   0.04641  -0.0606   0.0063   1.0000
  13.500   1.5264   0.05442   0.04933  -0.0602   0.0061   1.0000
  13.750   1.5269   0.05735   0.05234  -0.0600   0.0060   1.0000
  14.000   1.5269   0.06043   0.05552  -0.0599   0.0059   1.0000
  14.250   1.5263   0.06365   0.05883  -0.0600   0.0057   1.0000
  14.500   1.5251   0.06700   0.06225  -0.0602   0.0056   1.0000
  14.750   1.5224   0.07057   0.06590  -0.0605   0.0055   1.0000
  15.000   1.5184   0.07433   0.06975  -0.0607   0.0054   1.0000
  15.250   1.5130   0.07827   0.07377  -0.0609   0.0053   1.0000
  15.500   1.5060   0.08231   0.07790  -0.0608   0.0053   1.0000
  15.750   1.4953   0.08651   0.08223  -0.0599   0.0051   1.0000
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