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WACO COOTIE AIRFOIL (cootie-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: WACO COOTIE AIRFOIL (cootie-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.11 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cootie-il-1000000-n5.txt
Download as CSV file: xf-cootie-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3081   0.09922   0.09730  -0.0360   0.8839   0.0063
  -9.750  -0.3069   0.09476   0.09280  -0.0381   0.8751   0.0067
  -9.500  -0.3134   0.08833   0.08635  -0.0415   0.8668   0.0073
  -9.250  -0.3059   0.08554   0.08354  -0.0432   0.8602   0.0075
  -9.000  -0.2976   0.08283   0.08081  -0.0451   0.8536   0.0077
  -8.750  -0.2902   0.08005   0.07802  -0.0472   0.8471   0.0079
  -8.500  -0.2791   0.07669   0.07464  -0.0510   0.8414   0.0082
  -8.250  -0.2668   0.07233   0.07025  -0.0562   0.8354   0.0088
  -8.000  -0.2554   0.06398   0.06185  -0.0668   0.8298   0.0101
  -7.750  -0.2347   0.06115   0.05897  -0.0706   0.8243   0.0103
  -7.500  -0.2193   0.01699   0.01305  -0.1083   0.8198   0.0172
  -7.250  -0.1922   0.01613   0.01204  -0.1086   0.8153   0.0177
  -7.000  -0.1641   0.01609   0.01199  -0.1087   0.8101   0.0180
  -6.750  -0.1361   0.01607   0.01195  -0.1087   0.8048   0.0183
  -6.500  -0.1082   0.01595   0.01179  -0.1088   0.7996   0.0186
  -6.250  -0.0801   0.01580   0.01160  -0.1089   0.7935   0.0191
  -6.000  -0.0525   0.01516   0.01080  -0.1091   0.7874   0.0196
  -5.750  -0.0246   0.01454   0.01005  -0.1094   0.7808   0.0203
  -5.500   0.0033   0.01388   0.00922  -0.1095   0.7734   0.0209
  -5.250   0.0314   0.01319   0.00836  -0.1097   0.7658   0.0214
  -5.000   0.0594   0.01273   0.00774  -0.1098   0.7565   0.0218
  -4.750   0.0876   0.01235   0.00723  -0.1100   0.7457   0.0222
  -4.500   0.1157   0.01191   0.00664  -0.1101   0.7313   0.0224
  -4.250   0.1435   0.01153   0.00608  -0.1101   0.7105   0.0225
  -4.000   0.1711   0.01123   0.00558  -0.1101   0.6833   0.0226
  -3.750   0.1987   0.01098   0.00514  -0.1101   0.6579   0.0227
  -3.500   0.2264   0.01075   0.00475  -0.1101   0.6383   0.0228
  -3.250   0.2543   0.00993   0.00374  -0.1103   0.6252   0.0234
  -3.000   0.2825   0.00955   0.00326  -0.1104   0.6158   0.0238
  -2.750   0.3107   0.00929   0.00293  -0.1105   0.6077   0.0242
  -2.500   0.3392   0.00907   0.00267  -0.1107   0.6010   0.0247
  -2.250   0.3676   0.00892   0.00247  -0.1108   0.5941   0.0251
  -2.000   0.3961   0.00878   0.00229  -0.1109   0.5874   0.0257
  -1.750   0.4245   0.00868   0.00214  -0.1111   0.5803   0.0261
  -1.500   0.4530   0.00858   0.00201  -0.1112   0.5741   0.0266
  -1.250   0.4815   0.00849   0.00189  -0.1114   0.5678   0.0270
  -1.000   0.5099   0.00843   0.00180  -0.1115   0.5616   0.0273
  -0.750   0.5384   0.00837   0.00171  -0.1117   0.5545   0.0276
  -0.500   0.5667   0.00834   0.00164  -0.1118   0.5468   0.0279
  -0.250   0.5952   0.00830   0.00159  -0.1120   0.5392   0.0282
   0.000   0.6234   0.00830   0.00156  -0.1121   0.5319   0.0286
   0.250   0.6518   0.00829   0.00153  -0.1122   0.5242   0.0292
   0.500   0.6800   0.00831   0.00152  -0.1124   0.5159   0.0295
   0.750   0.7082   0.00834   0.00151  -0.1125   0.5061   0.0298
   1.000   0.7362   0.00838   0.00152  -0.1126   0.4954   0.0302
   1.250   0.7639   0.00846   0.00154  -0.1127   0.4802   0.0327
   1.500   0.7913   0.00856   0.00159  -0.1127   0.4609   0.0391
   1.750   0.8186   0.00863   0.00171  -0.1128   0.4439   0.0795
   2.000   0.8461   0.00875   0.00180  -0.1129   0.4300   0.0866
   2.250   0.8734   0.00887   0.00190  -0.1129   0.4157   0.0933
   2.500   0.9002   0.00905   0.00202  -0.1129   0.3971   0.0989
   2.750   0.9266   0.00928   0.00217  -0.1129   0.3732   0.1062
   3.000   0.9533   0.00946   0.00232  -0.1128   0.3561   0.1198
   3.250   0.9803   0.00955   0.00247  -0.1129   0.3438   0.1674
   3.750   1.0282   0.00849   0.00295  -0.1121   0.3181   1.0000
   4.000   1.0543   0.00876   0.00314  -0.1120   0.3005   1.0000
   4.250   1.0806   0.00900   0.00331  -0.1119   0.2863   1.0000
   4.500   1.1062   0.00931   0.00352  -0.1118   0.2670   1.0000
   4.750   1.1302   0.00978   0.00380  -0.1114   0.2330   1.0000
   5.000   1.1515   0.01053   0.00425  -0.1106   0.1796   1.0000
   5.250   1.1698   0.01158   0.00492  -0.1094   0.1113   1.0000
   5.500   1.1909   0.01230   0.00543  -0.1086   0.0759   1.0000
   5.750   1.2151   0.01267   0.00576  -0.1082   0.0644   1.0000
   6.000   1.2338   0.01359   0.00642  -0.1070   0.0221   1.0000
   6.250   1.2566   0.01406   0.00687  -0.1063   0.0139   1.0000
   6.500   1.2804   0.01440   0.00723  -0.1059   0.0117   1.0000
   6.750   1.3040   0.01474   0.00761  -0.1054   0.0108   1.0000
   7.000   1.3269   0.01513   0.00803  -0.1048   0.0097   1.0000
   7.250   1.3486   0.01561   0.00853  -0.1041   0.0085   1.0000
   7.500   1.3707   0.01602   0.00898  -0.1034   0.0079   1.0000
   7.750   1.3924   0.01644   0.00942  -0.1026   0.0074   1.0000
   8.000   1.4132   0.01690   0.00992  -0.1017   0.0069   1.0000
   8.250   1.4333   0.01740   0.01044  -0.1007   0.0064   1.0000
   8.500   1.4516   0.01799   0.01106  -0.0995   0.0059   1.0000
   8.750   1.4682   0.01864   0.01177  -0.0979   0.0056   1.0000
   9.000   1.4852   0.01919   0.01237  -0.0964   0.0054   1.0000
   9.250   1.4995   0.01977   0.01299  -0.0944   0.0052   1.0000
   9.500   1.5129   0.02040   0.01369  -0.0924   0.0049   1.0000
   9.750   1.5262   0.02108   0.01441  -0.0905   0.0046   1.0000
  10.000   1.5391   0.02182   0.01520  -0.0886   0.0044   1.0000
  10.250   1.5508   0.02267   0.01610  -0.0867   0.0042   1.0000
  10.500   1.5613   0.02365   0.01714  -0.0848   0.0041   1.0000
  10.750   1.5692   0.02487   0.01842  -0.0827   0.0039   1.0000
  11.000   1.5755   0.02627   0.01991  -0.0806   0.0037   1.0000
  11.250   1.5844   0.02751   0.02125  -0.0789   0.0037   1.0000
  11.500   1.5922   0.02890   0.02272  -0.0773   0.0036   1.0000
  11.750   1.5991   0.03042   0.02432  -0.0757   0.0035   1.0000
  12.000   1.6049   0.03207   0.02606  -0.0742   0.0034   1.0000
  12.250   1.6096   0.03390   0.02798  -0.0727   0.0033   1.0000
  12.500   1.6132   0.03588   0.03005  -0.0714   0.0033   1.0000
  12.750   1.6160   0.03800   0.03226  -0.0701   0.0032   1.0000
  13.000   1.6181   0.04028   0.03463  -0.0691   0.0031   1.0000
  13.250   1.6192   0.04274   0.03719  -0.0681   0.0030   1.0000
  13.500   1.6194   0.04537   0.03991  -0.0673   0.0030   1.0000
  13.750   1.6184   0.04825   0.04290  -0.0667   0.0029   1.0000
  14.000   1.6176   0.05123   0.04598  -0.0663   0.0029   1.0000
  14.250   1.6164   0.05435   0.04919  -0.0661   0.0028   1.0000
  14.500   1.6137   0.05775   0.05269  -0.0660   0.0028   1.0000
  14.750   1.6116   0.06118   0.05621  -0.0661   0.0027   1.0000
  15.000   1.6077   0.06492   0.06005  -0.0663   0.0027   1.0000
  15.250   1.6022   0.06891   0.06414  -0.0667   0.0026   1.0000
  15.500   1.5955   0.07318   0.06850  -0.0672   0.0026   1.0000
  15.750   1.5873   0.07775   0.07318  -0.0679   0.0025   1.0000
  16.000   1.5775   0.08266   0.07821  -0.0687   0.0025   1.0000
  16.250   1.5652   0.08803   0.08369  -0.0698   0.0024   1.0000
  16.500   1.5515   0.09372   0.08950  -0.0711   0.0024   1.0000
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