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WACO COOTIE AIRFOIL (cootie-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: WACO COOTIE AIRFOIL (cootie-il)
Reynolds number: 500,000
Max Cl/Cd: 116.02 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cootie-il-500000.txt
Download as CSV file: xf-cootie-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2876   0.10232   0.10013  -0.0334   1.0000   0.0187
  -9.250  -0.2843   0.09986   0.09770  -0.0337   1.0000   0.0191
  -9.000  -0.2803   0.09730   0.09518  -0.0347   0.9980   0.0196
  -8.750  -0.2632   0.09329   0.09116  -0.0395   0.9934   0.0207
  -8.500  -0.2462   0.08886   0.08673  -0.0499   0.9800   0.0220
  -8.250  -0.2266   0.08417   0.08202  -0.0581   0.9696   0.0221
  -8.000  -0.2083   0.07967   0.07750  -0.0643   0.9586   0.0222
  -7.750  -0.2007   0.07453   0.07235  -0.0663   0.9490   0.0226
  -7.500  -0.1877   0.07198   0.06977  -0.0663   0.9409   0.0230
  -7.250  -0.1735   0.06934   0.06710  -0.0679   0.9314   0.0235
  -7.000  -0.1571   0.06642   0.06412  -0.0708   0.9229   0.0242
  -6.750  -0.1385   0.06318   0.06081  -0.0745   0.9146   0.0253
  -6.500  -0.0994   0.05816   0.05564  -0.0858   0.9061   0.0281
  -6.250  -0.0730   0.05380   0.05115  -0.0907   0.8991   0.0283
  -6.000  -0.0589   0.04826   0.04554  -0.0936   0.8922   0.0292
  -5.750  -0.0389   0.04626   0.04348  -0.0944   0.8855   0.0299
  -5.500  -0.0157   0.04402   0.04116  -0.0960   0.8792   0.0309
  -5.250   0.0116   0.04121   0.03823  -0.0986   0.8722   0.0334
  -5.000   0.0501   0.03428   0.03087  -0.1047   0.8666   0.0372
  -4.750   0.0729   0.03278   0.02933  -0.1051   0.8593   0.0381
  -4.500   0.0975   0.03135   0.02779  -0.1056   0.8529   0.0395
  -4.250   0.1256   0.02928   0.02558  -0.1067   0.8456   0.0426
  -4.000   0.1561   0.02584   0.02178  -0.1082   0.8389   0.0479
  -3.750   0.1818   0.02487   0.02075  -0.1085   0.8306   0.0498
  -3.500   0.2129   0.02246   0.01788  -0.1091   0.8225   0.0578
  -3.250   0.2386   0.02133   0.01673  -0.1093   0.8114   0.0592
  -3.000   0.2719   0.01481   0.00929  -0.1097   0.8027   0.0432
  -2.750   0.3007   0.01223   0.00617  -0.1096   0.7925   0.0401
  -2.500   0.3289   0.01139   0.00515  -0.1095   0.7808   0.0399
  -2.250   0.3570   0.01080   0.00442  -0.1094   0.7696   0.0400
  -2.000   0.3850   0.01034   0.00385  -0.1093   0.7580   0.0403
  -1.750   0.4128   0.01001   0.00344  -0.1092   0.7450   0.0412
  -1.500   0.4407   0.00972   0.00306  -0.1091   0.7313   0.0421
  -1.250   0.4686   0.00947   0.00273  -0.1091   0.7174   0.0426
  -1.000   0.4965   0.00929   0.00247  -0.1090   0.7034   0.0436
  -0.500   0.5523   0.00911   0.00212  -0.1089   0.6767   0.0463
  -0.250   0.5804   0.00906   0.00203  -0.1089   0.6651   0.0505
   0.000   0.6083   0.00903   0.00204  -0.1089   0.6549   0.0653
   0.250   0.6360   0.00912   0.00212  -0.1089   0.6451   0.0914
   0.500   0.6640   0.00920   0.00220  -0.1089   0.6352   0.1038
   0.750   0.6917   0.00930   0.00225  -0.1089   0.6261   0.1108
   1.000   0.7194   0.00935   0.00229  -0.1089   0.6171   0.1179
   1.250   0.7473   0.00940   0.00233  -0.1090   0.6086   0.1246
   1.750   0.8028   0.00947   0.00242  -0.1092   0.5915   0.1405
   2.000   0.8304   0.00950   0.00248  -0.1092   0.5827   0.1582
   2.250   0.8523   0.00788   0.00266  -0.1083   0.5737   1.0000
   2.500   0.8798   0.00801   0.00273  -0.1083   0.5633   1.0000
   2.750   0.9070   0.00814   0.00280  -0.1083   0.5515   1.0000
   3.000   0.9341   0.00829   0.00288  -0.1082   0.5389   1.0000
   3.250   0.9610   0.00844   0.00297  -0.1081   0.5251   1.0000
   3.500   0.9878   0.00860   0.00309  -0.1080   0.5101   1.0000
   3.750   1.0144   0.00877   0.00321  -0.1079   0.4938   1.0000
   4.000   1.0407   0.00897   0.00336  -0.1078   0.4755   1.0000
   4.250   1.0665   0.00922   0.00353  -0.1075   0.4554   1.0000
   4.500   1.0918   0.00951   0.00373  -0.1073   0.4328   1.0000
   4.750   1.1163   0.00987   0.00396  -0.1069   0.4079   1.0000
   5.000   1.1411   0.01021   0.00420  -0.1066   0.3852   1.0000
   5.250   1.1657   0.01057   0.00448  -0.1062   0.3657   1.0000
   5.500   1.1902   0.01092   0.00477  -0.1058   0.3480   1.0000
   5.750   1.2146   0.01127   0.00506  -0.1055   0.3292   1.0000
   6.000   1.2387   0.01165   0.00537  -0.1051   0.3100   1.0000
   6.250   1.2621   0.01207   0.00572  -0.1046   0.2900   1.0000
   6.500   1.2848   0.01256   0.00609  -0.1040   0.2601   1.0000
   6.750   1.3000   0.01373   0.00678  -0.1024   0.1815   1.0000
   7.000   1.3077   0.01558   0.00802  -0.0997   0.0897   1.0000
   7.250   1.3244   0.01653   0.00881  -0.0982   0.0618   1.0000
   7.500   1.3361   0.01786   0.00986  -0.0959   0.0228   1.0000
   7.750   1.3539   0.01860   0.01064  -0.0945   0.0195   1.0000
   8.000   1.3718   0.01928   0.01141  -0.0931   0.0180   1.0000
   8.250   1.3881   0.02002   0.01224  -0.0914   0.0169   1.0000
   8.500   1.4017   0.02087   0.01318  -0.0894   0.0160   1.0000
   8.750   1.4104   0.02185   0.01426  -0.0865   0.0153   1.0000
   9.000   1.4159   0.02308   0.01559  -0.0833   0.0147   1.0000
   9.250   1.4173   0.02466   0.01729  -0.0799   0.0142   1.0000
   9.500   1.4196   0.02629   0.01903  -0.0770   0.0139   1.0000
   9.750   1.4266   0.02766   0.02049  -0.0748   0.0137   1.0000
  10.000   1.4328   0.02917   0.02210  -0.0728   0.0134   1.0000
  10.250   1.4378   0.03085   0.02387  -0.0709   0.0131   1.0000
  10.500   1.4421   0.03266   0.02579  -0.0690   0.0127   1.0000
  10.750   1.4453   0.03463   0.02785  -0.0673   0.0123   1.0000
  11.000   1.4473   0.03679   0.03009  -0.0657   0.0120   1.0000
  11.250   1.4487   0.03908   0.03247  -0.0641   0.0117   1.0000
  11.500   1.4497   0.04147   0.03495  -0.0627   0.0115   1.0000
  11.750   1.4504   0.04395   0.03751  -0.0614   0.0113   1.0000
  12.000   1.4507   0.04651   0.04014  -0.0601   0.0111   1.0000
  12.250   1.4515   0.04907   0.04277  -0.0588   0.0110   1.0000
  12.500   1.4527   0.05159   0.04537  -0.0573   0.0108   1.0000
  12.750   1.4560   0.05393   0.04775  -0.0556   0.0106   1.0000
  13.000   1.4642   0.05596   0.04984  -0.0534   0.0105   1.0000
  13.250   1.4783   0.05800   0.05196  -0.0512   0.0103   1.0000
  13.500   1.4891   0.06052   0.05462  -0.0496   0.0103   1.0000
  13.750   1.4833   0.06369   0.05797  -0.0490   0.0102   1.0000
  14.000   1.4766   0.06704   0.06150  -0.0488   0.0102   1.0000
  14.250   1.4705   0.07058   0.06523  -0.0487   0.0101   1.0000
  14.500   1.4636   0.07438   0.06921  -0.0490   0.0100   1.0000
  14.750   1.4568   0.07841   0.07342  -0.0495   0.0099   1.0000
  15.000   1.4492   0.08272   0.07793  -0.0501   0.0098   1.0000
  15.250   1.4407   0.08732   0.08270  -0.0511   0.0097   1.0000
  15.500   1.4311   0.09219   0.08775  -0.0522   0.0097   1.0000
  15.750   1.4205   0.09741   0.09315  -0.0536   0.0097   1.0000
  16.000   1.4090   0.10293   0.09885  -0.0554   0.0097   1.0000
  16.250   1.3964   0.10881   0.10490  -0.0574   0.0098   1.0000
  16.500   1.3827   0.11502   0.11128  -0.0598   0.0099   1.0000
  16.750   1.3682   0.12159   0.11803  -0.0625   0.0100   1.0000
  17.000   1.3809   0.12287   0.11932  -0.0614   0.0106   1.0000
  17.250   1.1174   0.11864   0.11537  -0.0421   0.0106   1.0000
  17.500   1.0995   0.12396   0.12085  -0.0450   0.0107   1.0000
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