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WACO COOTIE AIRFOIL (cootie-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: WACO COOTIE AIRFOIL (cootie-il)
Reynolds number: 200,000
Max Cl/Cd: 84.02 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cootie-il-200000.txt
Download as CSV file: xf-cootie-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2939   0.10362   0.10030  -0.0344   1.0000   0.0357
  -8.750  -0.3144   0.10374   0.10052  -0.0305   1.0000   0.0358
  -8.500  -0.3377   0.10400   0.10088  -0.0257   1.0000   0.0359
  -8.250  -0.3446   0.10265   0.09960  -0.0281   0.9974   0.0360
  -7.750  -0.3085   0.09174   0.08866  -0.0341   0.9908   0.0373
  -7.500  -0.2876   0.08780   0.08471  -0.0367   0.9871   0.0386
  -7.250  -0.2612   0.08373   0.08061  -0.0428   0.9835   0.0410
  -7.000  -0.2262   0.07942   0.07623  -0.0565   0.9749   0.0452
  -6.750  -0.1866   0.07285   0.06956  -0.0704   0.9707   0.0464
  -6.500  -0.1738   0.06950   0.06623  -0.0685   0.9653   0.0475
  -6.250  -0.1465   0.06602   0.06271  -0.0721   0.9610   0.0499
  -5.750  -0.0661   0.05653   0.05297  -0.0906   0.9514   0.0582
  -5.500  -0.0388   0.05355   0.04996  -0.0930   0.9466   0.0607
  -5.250   0.0242   0.04902   0.04491  -0.1065   0.9426   0.0687
  -5.000   0.0402   0.04548   0.04147  -0.1061   0.9349   0.0699
  -4.750   0.0667   0.04304   0.03903  -0.1074   0.9297   0.0731
  -4.500   0.1140   0.04060   0.03597  -0.1135   0.9223   0.0817
  -4.250   0.1358   0.03692   0.03239  -0.1141   0.9154   0.0832
  -4.000   0.1601   0.03474   0.03016  -0.1145   0.9077   0.0854
  -3.750   0.1884   0.03273   0.02799  -0.1153   0.8998   0.0898
  -3.500   0.2209   0.03053   0.02536  -0.1167   0.8908   0.0969
  -3.250   0.2460   0.02851   0.02330  -0.1168   0.8833   0.0993
  -3.000   0.2721   0.02695   0.02157  -0.1167   0.8728   0.1029
  -2.750   0.3114   0.02182   0.01538  -0.1172   0.8665   0.0700
  -2.500   0.3386   0.02009   0.01339  -0.1167   0.8558   0.0658
  -2.250   0.3659   0.01872   0.01171  -0.1161   0.8449   0.0664
  -2.000   0.3933   0.01731   0.01001  -0.1154   0.8345   0.0657
  -1.750   0.4205   0.01612   0.00855  -0.1148   0.8235   0.0654
  -1.500   0.4475   0.01524   0.00748  -0.1142   0.8119   0.0663
  -1.250   0.4748   0.01458   0.00669  -0.1137   0.8018   0.0678
  -1.000   0.5021   0.01392   0.00598  -0.1132   0.7928   0.0709
  -0.750   0.5291   0.01367   0.00573  -0.1129   0.7812   0.0766
  -0.500   0.5564   0.01337   0.00543  -0.1126   0.7707   0.0855
  -0.250   0.5840   0.01304   0.00508  -0.1122   0.7612   0.1067
   0.000   0.6112   0.01279   0.00485  -0.1120   0.7502   0.1333
   0.250   0.6383   0.01268   0.00472  -0.1118   0.7393   0.1501
   0.500   0.6656   0.01253   0.00457  -0.1117   0.7290   0.1617
   0.750   0.6930   0.01241   0.00443  -0.1115   0.7190   0.1794
   1.000   0.7201   0.01230   0.00438  -0.1114   0.7074   0.1960
   1.250   0.7430   0.01057   0.00441  -0.1103   0.6970   1.0000
   1.500   0.7706   0.01070   0.00435  -0.1100   0.6869   1.0000
   1.750   0.7978   0.01084   0.00434  -0.1097   0.6760   1.0000
   2.000   0.8247   0.01100   0.00440  -0.1095   0.6643   1.0000
   2.250   0.8516   0.01118   0.00447  -0.1093   0.6528   1.0000
   2.500   0.8786   0.01138   0.00458  -0.1090   0.6419   1.0000
   2.750   0.9055   0.01159   0.00469  -0.1088   0.6309   1.0000
   3.000   0.9319   0.01180   0.00487  -0.1086   0.6185   1.0000
   3.250   0.9582   0.01202   0.00505  -0.1083   0.6059   1.0000
   3.500   0.9845   0.01226   0.00525  -0.1081   0.5934   1.0000
   3.750   1.0105   0.01248   0.00544  -0.1077   0.5800   1.0000
   4.000   1.0361   0.01269   0.00562  -0.1074   0.5654   1.0000
   4.250   1.0615   0.01290   0.00581  -0.1069   0.5499   1.0000
   4.500   1.0867   0.01311   0.00601  -0.1065   0.5344   1.0000
   4.750   1.1116   0.01332   0.00620  -0.1060   0.5177   1.0000
   5.000   1.1362   0.01355   0.00641  -0.1055   0.5009   1.0000
   5.250   1.1608   0.01382   0.00667  -0.1050   0.4850   1.0000
   5.500   1.1847   0.01410   0.00692  -0.1043   0.4679   1.0000
   5.750   1.2080   0.01440   0.00720  -0.1037   0.4489   1.0000
   6.000   1.2306   0.01473   0.00749  -0.1029   0.4279   1.0000
   6.250   1.2525   0.01513   0.00783  -0.1020   0.4078   1.0000
   6.500   1.2750   0.01551   0.00823  -0.1012   0.3898   1.0000
   6.750   1.2966   0.01593   0.00865  -0.1004   0.3703   1.0000
   7.000   1.3167   0.01645   0.00910  -0.0993   0.3492   1.0000
   7.250   1.3363   0.01695   0.00961  -0.0981   0.3239   1.0000
   7.500   1.3558   0.01750   0.01014  -0.0970   0.3012   1.0000
   7.750   1.3736   0.01813   0.01072  -0.0956   0.2701   1.0000
   8.000   1.3852   0.01917   0.01148  -0.0933   0.2108   1.0000
   8.250   1.3834   0.02129   0.01296  -0.0894   0.1242   1.0000
   8.500   1.3825   0.02326   0.01455  -0.0856   0.0764   1.0000
   8.750   1.3842   0.02479   0.01596  -0.0819   0.0477   1.0000
   9.000   1.3882   0.02626   0.01736  -0.0788   0.0362   1.0000
   9.250   1.3926   0.02778   0.01892  -0.0759   0.0322   1.0000
   9.500   1.3980   0.02928   0.02055  -0.0735   0.0302   1.0000
   9.750   1.4025   0.03092   0.02232  -0.0712   0.0285   1.0000
  10.000   1.4049   0.03279   0.02432  -0.0689   0.0270   1.0000
  10.250   1.4039   0.03506   0.02669  -0.0667   0.0258   1.0000
  10.500   1.4002   0.03768   0.02943  -0.0646   0.0251   1.0000
  10.750   1.3950   0.04058   0.03245  -0.0625   0.0246   1.0000
  11.000   1.3942   0.04316   0.03517  -0.0609   0.0243   1.0000
  11.250   1.3944   0.04574   0.03787  -0.0595   0.0240   1.0000
  11.500   1.3949   0.04833   0.04058  -0.0581   0.0237   1.0000
  11.750   1.3963   0.05088   0.04324  -0.0568   0.0235   1.0000
  12.000   1.3990   0.05335   0.04581  -0.0554   0.0232   1.0000
  12.250   1.4034   0.05568   0.04825  -0.0539   0.0230   1.0000
  12.500   1.4091   0.05794   0.05062  -0.0525   0.0226   1.0000
  12.750   1.4150   0.06024   0.05304  -0.0513   0.0221   1.0000
  13.000   1.4205   0.06261   0.05555  -0.0502   0.0216   1.0000
  13.250   1.4253   0.06513   0.05820  -0.0491   0.0210   1.0000
  13.500   1.4308   0.06777   0.06100  -0.0479   0.0209   1.0000
  13.750   1.4346   0.07073   0.06417  -0.0469   0.0209   1.0000
  14.000   1.4342   0.07424   0.06792  -0.0461   0.0210   1.0000
  14.250   1.4301   0.07826   0.07222  -0.0456   0.0212   1.0000
  14.500   1.4221   0.08286   0.07711  -0.0455   0.0214   1.0000
  14.750   1.4106   0.08800   0.08253  -0.0459   0.0217   1.0000
  15.000   1.3963   0.09364   0.08845  -0.0470   0.0220   1.0000
  15.250   1.3803   0.09973   0.09480  -0.0486   0.0223   1.0000
  15.500   1.3633   0.10624   0.10155  -0.0509   0.0226   1.0000
  15.750   1.3453   0.11315   0.10869  -0.0538   0.0229   1.0000
  16.000   1.3268   0.12049   0.11624  -0.0573   0.0232   1.0000
  16.250   1.3081   0.12829   0.12423  -0.0616   0.0234   1.0000
  16.500   1.2891   0.13659   0.13272  -0.0664   0.0237   1.0000
  16.750   1.2700   0.14540   0.14169  -0.0719   0.0240   1.0000
  17.000   1.2589   0.15254   0.14892  -0.0750   0.0246   1.0000
  17.250   1.2462   0.16088   0.15743  -0.0813   0.0249   1.0000
  17.500   1.1969   0.18337   0.18022  -0.0980   0.0259   1.0000
  17.750   0.9012   0.16754   0.16461  -0.0680   0.0263   1.0000
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