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WACO COOTIE AIRFOIL (cootie-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: WACO COOTIE AIRFOIL (cootie-il)
Reynolds number: 500,000
Max Cl/Cd: 107.56 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cootie-il-500000-n5.txt
Download as CSV file: xf-cootie-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2733   0.09533   0.09305  -0.0424   0.9426   0.0094
  -9.250  -0.2715   0.09067   0.08835  -0.0447   0.9246   0.0097
  -9.000  -0.2681   0.08698   0.08462  -0.0465   0.9112   0.0100
  -8.750  -0.2590   0.08484   0.08244  -0.0477   0.9009   0.0103
  -8.500  -0.2496   0.08270   0.08026  -0.0490   0.8917   0.0106
  -8.250  -0.2416   0.08005   0.07760  -0.0510   0.8833   0.0111
  -7.750  -0.2184   0.07180   0.06928  -0.0601   0.8683   0.0121
  -7.250  -0.1840   0.06076   0.05811  -0.0740   0.8550   0.0136
  -7.000  -0.1626   0.05879   0.05609  -0.0765   0.8491   0.0141
  -6.750  -0.1397   0.05567   0.05290  -0.0805   0.8434   0.0149
  -6.500  -0.1065   0.04336   0.04030  -0.0944   0.8372   0.0174
  -6.000  -0.0563   0.04068   0.03747  -0.0974   0.8258   0.0185
  -5.750  -0.0288   0.03788   0.03453  -0.0999   0.8196   0.0194
  -5.500   0.0076   0.02058   0.01601  -0.1092   0.8155   0.0233
  -5.250   0.0346   0.01884   0.01404  -0.1098   0.8090   0.0239
  -5.000   0.0619   0.01776   0.01276  -0.1102   0.8026   0.0246
  -4.750   0.0896   0.01694   0.01179  -0.1105   0.7955   0.0254
  -4.500   0.1174   0.01569   0.01026  -0.1107   0.7882   0.0261
  -4.250   0.1455   0.01456   0.00887  -0.1110   0.7804   0.0265
  -4.000   0.1735   0.01368   0.00774  -0.1111   0.7719   0.0269
  -3.750   0.2017   0.01294   0.00682  -0.1112   0.7620   0.0272
  -3.500   0.2297   0.01238   0.00608  -0.1113   0.7499   0.0277
  -3.250   0.2576   0.01193   0.00546  -0.1112   0.7339   0.0283
  -3.000   0.2850   0.01150   0.00484  -0.1111   0.7129   0.0286
  -2.750   0.3124   0.01115   0.00430  -0.1110   0.6896   0.0288
  -2.500   0.3399   0.01089   0.00386  -0.1108   0.6706   0.0292
  -2.250   0.3676   0.01066   0.00351  -0.1108   0.6567   0.0295
  -2.000   0.3955   0.01048   0.00323  -0.1108   0.6452   0.0298
  -1.750   0.4233   0.01034   0.00300  -0.1108   0.6347   0.0301
  -1.500   0.4512   0.01014   0.00273  -0.1109   0.6254   0.0305
  -1.250   0.4793   0.00995   0.00249  -0.1109   0.6174   0.0310
  -1.000   0.5073   0.00985   0.00232  -0.1110   0.6092   0.0316
  -0.750   0.5354   0.00976   0.00220  -0.1111   0.6012   0.0323
  -0.500   0.5634   0.00972   0.00211  -0.1111   0.5936   0.0335
  -0.250   0.5916   0.00967   0.00204  -0.1113   0.5866   0.0346
   0.000   0.6196   0.00966   0.00200  -0.1113   0.5794   0.0352
   0.250   0.6477   0.00965   0.00196  -0.1114   0.5720   0.0362
   0.500   0.6756   0.00966   0.00195  -0.1115   0.5639   0.0376
   1.000   0.7314   0.00965   0.00203  -0.1117   0.5478   0.0764
   1.250   0.7594   0.00969   0.00209  -0.1118   0.5396   0.0879
   1.500   0.7870   0.00975   0.00215  -0.1118   0.5311   0.0950
   1.750   0.8146   0.00982   0.00222  -0.1119   0.5210   0.1004
   2.000   0.8421   0.00989   0.00229  -0.1119   0.5094   0.1067
   2.250   0.8691   0.00999   0.00238  -0.1119   0.4936   0.1195
   2.500   0.8959   0.01009   0.00250  -0.1119   0.4767   0.1399
   2.750   0.9229   0.00980   0.00272  -0.1123   0.4623   0.4243
   3.250   0.9702   0.00902   0.00300  -0.1108   0.4336   1.0000
   3.500   0.9959   0.00930   0.00316  -0.1106   0.4133   1.0000
   3.750   1.0216   0.00958   0.00335  -0.1104   0.3930   1.0000
   4.000   1.0474   0.00986   0.00356  -0.1102   0.3764   1.0000
   4.250   1.0728   0.01015   0.00377  -0.1100   0.3596   1.0000
   4.500   1.0974   0.01053   0.00403  -0.1096   0.3385   1.0000
   4.750   1.1222   0.01088   0.00429  -0.1093   0.3189   1.0000
   5.000   1.1468   0.01124   0.00457  -0.1090   0.2999   1.0000
   5.250   1.1712   0.01160   0.00486  -0.1087   0.2812   1.0000
   5.500   1.1945   0.01206   0.00518  -0.1082   0.2530   1.0000
   5.750   1.2156   0.01273   0.00562  -0.1074   0.2093   1.0000
   6.000   1.2320   0.01384   0.00636  -0.1059   0.1464   1.0000
   6.250   1.2456   0.01518   0.00730  -0.1041   0.0803   1.0000
   6.500   1.2655   0.01587   0.00788  -0.1030   0.0600   1.0000
   6.750   1.2801   0.01700   0.00876  -0.1012   0.0190   1.0000
   7.000   1.3004   0.01757   0.00938  -0.1002   0.0150   1.0000
   7.250   1.3199   0.01818   0.01005  -0.0991   0.0126   1.0000
   7.500   1.3397   0.01872   0.01066  -0.0980   0.0116   1.0000
   7.750   1.3588   0.01928   0.01129  -0.0968   0.0109   1.0000
   8.000   1.3764   0.01990   0.01199  -0.0954   0.0101   1.0000
   8.250   1.3923   0.02058   0.01275  -0.0938   0.0094   1.0000
   8.500   1.4037   0.02139   0.01363  -0.0914   0.0087   1.0000
   8.750   1.4131   0.02236   0.01468  -0.0887   0.0081   1.0000
   9.000   1.4252   0.02319   0.01560  -0.0867   0.0079   1.0000
   9.250   1.4362   0.02414   0.01663  -0.0846   0.0075   1.0000
   9.500   1.4458   0.02523   0.01781  -0.0826   0.0072   1.0000
   9.750   1.4545   0.02643   0.01910  -0.0805   0.0069   1.0000
  10.000   1.4623   0.02776   0.02053  -0.0786   0.0067   1.0000
  10.250   1.4692   0.02921   0.02206  -0.0767   0.0064   1.0000
  10.500   1.4754   0.03078   0.02371  -0.0750   0.0062   1.0000
  10.750   1.4801   0.03253   0.02555  -0.0733   0.0060   1.0000
  11.000   1.4803   0.03477   0.02788  -0.0715   0.0058   1.0000
  11.250   1.4791   0.03724   0.03045  -0.0697   0.0056   1.0000
  11.500   1.4834   0.03926   0.03258  -0.0686   0.0055   1.0000
  11.750   1.4863   0.04150   0.03493  -0.0675   0.0053   1.0000
  12.000   1.4873   0.04401   0.03756  -0.0665   0.0052   1.0000
  12.250   1.4865   0.04680   0.04046  -0.0656   0.0050   1.0000
  12.500   1.4850   0.04977   0.04356  -0.0649   0.0049   1.0000
  12.750   1.4832   0.05286   0.04677  -0.0643   0.0048   1.0000
  13.000   1.4810   0.05608   0.05011  -0.0639   0.0047   1.0000
  13.250   1.4786   0.05944   0.05358  -0.0637   0.0046   1.0000
  13.500   1.4761   0.06291   0.05716  -0.0637   0.0045   1.0000
  13.750   1.4728   0.06652   0.06088  -0.0637   0.0044   1.0000
  14.000   1.4695   0.07021   0.06467  -0.0639   0.0044   1.0000
  14.250   1.4663   0.07397   0.06854  -0.0642   0.0043   1.0000
  14.500   1.4623   0.07791   0.07259  -0.0646   0.0042   1.0000
  14.750   1.4581   0.08192   0.07670  -0.0652   0.0042   1.0000
  15.000   1.4535   0.08605   0.08094  -0.0659   0.0041   1.0000
  15.250   1.4485   0.09032   0.08531  -0.0667   0.0041   1.0000
  15.500   1.4433   0.09469   0.08978  -0.0676   0.0040   1.0000
  15.750   1.4375   0.09918   0.09439  -0.0686   0.0040   1.0000
  16.000   1.4314   0.10373   0.09906  -0.0697   0.0039   1.0000
  16.250   1.4248   0.10842   0.10386  -0.0709   0.0039   1.0000
  16.500   1.4172   0.11328   0.10883  -0.0722   0.0038   1.0000
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