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cr001sm (cr001sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: cr001sm (cr001sm-il)
Reynolds number: 500,000
Max Cl/Cd: 105.23 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cr001sm-il-500000-n5.txt
Download as CSV file: xf-cr001sm-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: cr001sm                                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3585   0.10024   0.09796  -0.0289   1.0000   0.0100
  -8.500  -0.3587   0.09767   0.09541  -0.0285   1.0000   0.0100
  -8.250  -0.3607   0.09517   0.09295  -0.0278   1.0000   0.0100
  -8.000  -0.3492   0.09115   0.08894  -0.0313   0.9984   0.0100
  -7.750  -0.3348   0.08697   0.08477  -0.0356   0.9955   0.0100
  -7.500  -0.3224   0.08290   0.08070  -0.0397   0.9913   0.0100
  -7.000  -0.2908   0.07461   0.07240  -0.0486   0.9835   0.0095
  -6.750  -0.2731   0.07039   0.06818  -0.0541   0.9783   0.0090
  -6.500  -0.2475   0.06485   0.06262  -0.0629   0.9744   0.0086
  -6.250  -0.2214   0.05900   0.05673  -0.0721   0.9693   0.0081
  -6.000  -0.1905   0.05228   0.04994  -0.0826   0.9635   0.0081
  -5.750  -0.1501   0.04426   0.04177  -0.0950   0.9601   0.0083
  -5.500  -0.1154   0.03649   0.03374  -0.1037   0.9537   0.0085
  -5.250  -0.0795   0.02848   0.02527  -0.1105   0.9485   0.0087
  -5.000  -0.0452   0.02144   0.01757  -0.1144   0.9443   0.0095
  -4.750  -0.0188   0.01730   0.01281  -0.1151   0.9368   0.0096
  -4.500   0.0133   0.01465   0.00965  -0.1165   0.9324   0.0098
  -4.250   0.0414   0.01327   0.00796  -0.1166   0.9255   0.0100
  -4.000   0.0719   0.01184   0.00627  -0.1173   0.9196   0.0107
  -3.750   0.1010   0.01128   0.00562  -0.1176   0.9124   0.0113
  -3.500   0.1316   0.01073   0.00496  -0.1182   0.9052   0.0121
  -3.250   0.1599   0.01020   0.00433  -0.1182   0.8965   0.0130
  -3.000   0.1896   0.00991   0.00394  -0.1185   0.8882   0.0143
  -2.750   0.2174   0.00932   0.00326  -0.1184   0.8785   0.0157
  -2.500   0.2451   0.00895   0.00283  -0.1183   0.8684   0.0170
  -2.250   0.2731   0.00869   0.00250  -0.1183   0.8579   0.0185
  -2.000   0.3009   0.00848   0.00220  -0.1181   0.8469   0.0201
  -1.750   0.3282   0.00830   0.00194  -0.1179   0.8350   0.0222
  -1.500   0.3552   0.00811   0.00168  -0.1175   0.8223   0.0252
  -1.250   0.3822   0.00801   0.00151  -0.1172   0.8095   0.0288
  -1.000   0.4088   0.00790   0.00136  -0.1168   0.7959   0.0413
  -0.750   0.4349   0.00764   0.00127  -0.1165   0.7819   0.1147
  -0.500   0.4605   0.00739   0.00123  -0.1161   0.7672   0.2147
  -0.250   0.4860   0.00720   0.00123  -0.1156   0.7516   0.3085
   0.000   0.5097   0.00680   0.00130  -0.1150   0.7349   0.5025
   0.250   0.5313   0.00639   0.00139  -0.1136   0.7162   0.6963
   0.750   0.5922   0.00607   0.00139  -0.1143   0.6700   1.0000
   1.000   0.6170   0.00623   0.00141  -0.1136   0.6474   1.0000
   1.250   0.6420   0.00640   0.00145  -0.1129   0.6255   1.0000
   1.500   0.6670   0.00657   0.00150  -0.1122   0.6043   1.0000
   1.750   0.6919   0.00676   0.00157  -0.1115   0.5826   1.0000
   2.000   0.7169   0.00694   0.00164  -0.1109   0.5618   1.0000
   2.250   0.7419   0.00713   0.00173  -0.1103   0.5409   1.0000
   2.500   0.7669   0.00733   0.00183  -0.1096   0.5204   1.0000
   2.750   0.7917   0.00754   0.00196  -0.1090   0.4986   1.0000
   3.000   0.8166   0.00776   0.00208  -0.1084   0.4775   1.0000
   3.250   0.8411   0.00800   0.00222  -0.1077   0.4538   1.0000
   3.500   0.8657   0.00824   0.00238  -0.1070   0.4305   1.0000
   3.750   0.8900   0.00851   0.00255  -0.1064   0.4060   1.0000
   4.000   0.9140   0.00881   0.00275  -0.1056   0.3785   1.0000
   4.250   0.9376   0.00915   0.00297  -0.1049   0.3485   1.0000
   4.500   0.9608   0.00953   0.00320  -0.1041   0.3159   1.0000
   4.750   0.9838   0.00994   0.00347  -0.1032   0.2838   1.0000
   5.000   1.0068   0.01035   0.00377  -0.1024   0.2545   1.0000
   5.500   1.0527   0.01118   0.00439  -0.1007   0.2020   1.0000
   5.750   1.0757   0.01159   0.00471  -0.0999   0.1799   1.0000
   6.000   1.0982   0.01204   0.00506  -0.0991   0.1577   1.0000
   6.250   1.1202   0.01253   0.00546  -0.0981   0.1327   1.0000
   6.500   1.1417   0.01306   0.00587  -0.0971   0.1075   1.0000
   6.750   1.1632   0.01359   0.00630  -0.0961   0.0861   1.0000
   7.000   1.1840   0.01417   0.00678  -0.0950   0.0673   1.0000
   7.250   1.2052   0.01470   0.00727  -0.0940   0.0530   1.0000
   7.500   1.2260   0.01526   0.00780  -0.0929   0.0409   1.0000
   7.750   1.2464   0.01584   0.00836  -0.0917   0.0310   1.0000
   8.000   1.2663   0.01645   0.00895  -0.0904   0.0232   1.0000
   8.250   1.2859   0.01708   0.00959  -0.0891   0.0182   1.0000
   8.500   1.3060   0.01764   0.01020  -0.0879   0.0157   1.0000
   8.750   1.3248   0.01828   0.01090  -0.0865   0.0134   1.0000
   9.000   1.3428   0.01899   0.01166  -0.0849   0.0115   1.0000
   9.250   1.3612   0.01960   0.01236  -0.0835   0.0106   1.0000
   9.500   1.3785   0.02028   0.01312  -0.0818   0.0097   1.0000
   9.750   1.3943   0.02103   0.01393  -0.0800   0.0088   1.0000
  10.000   1.4053   0.02202   0.01501  -0.0774   0.0079   1.0000
  10.250   1.4191   0.02270   0.01579  -0.0752   0.0075   1.0000
  10.500   1.4323   0.02342   0.01660  -0.0730   0.0069   1.0000
  10.750   1.4433   0.02429   0.01758  -0.0706   0.0064   1.0000
  11.000   1.4539   0.02518   0.01856  -0.0682   0.0060   1.0000
  11.250   1.4625   0.02622   0.01970  -0.0656   0.0057   1.0000
  11.500   1.4681   0.02751   0.02109  -0.0628   0.0054   1.0000
  11.750   1.4694   0.02915   0.02286  -0.0597   0.0050   1.0000
  12.000   1.4752   0.03049   0.02433  -0.0573   0.0049   1.0000
  12.250   1.4792   0.03203   0.02601  -0.0549   0.0048   1.0000
  12.500   1.4824   0.03369   0.02781  -0.0527   0.0046   1.0000
  12.750   1.4846   0.03553   0.02979  -0.0507   0.0045   1.0000
  13.000   1.4853   0.03760   0.03201  -0.0488   0.0043   1.0000
  13.250   1.4846   0.03991   0.03447  -0.0472   0.0042   1.0000
  13.500   1.4831   0.04243   0.03716  -0.0459   0.0041   1.0000
  13.750   1.4815   0.04511   0.03999  -0.0449   0.0039   1.0000
  14.000   1.4762   0.04836   0.04340  -0.0442   0.0039   1.0000
  14.250   1.4715   0.05175   0.04694  -0.0439   0.0038   1.0000
  14.500   1.4659   0.05544   0.05079  -0.0441   0.0037   1.0000
  14.750   1.4583   0.05962   0.05513  -0.0447   0.0037   1.0000
  15.000   1.4497   0.06421   0.05987  -0.0457   0.0036   1.0000
  15.250   1.4402   0.06922   0.06504  -0.0473   0.0036   1.0000
  15.500   1.4297   0.07465   0.07063  -0.0493   0.0035   1.0000
  15.750   1.4174   0.08069   0.07683  -0.0518   0.0035   1.0000
  16.000   1.4040   0.08723   0.08354  -0.0548   0.0035   1.0000
  16.250   1.3895   0.09428   0.09074  -0.0583   0.0035   1.0000
  16.500   1.3733   0.10194   0.09857  -0.0622   0.0035   1.0000
  16.750   1.3568   0.10997   0.10676  -0.0665   0.0035   1.0000
  17.000   1.3404   0.11826   0.11520  -0.0711   0.0035   1.0000
  17.250   1.3237   0.12685   0.12394  -0.0760   0.0035   1.0000
  17.500   1.3066   0.13580   0.13304  -0.0812   0.0035   1.0000
  17.750   1.2897   0.14491   0.14229  -0.0866   0.0035   1.0000
  18.000   1.2735   0.15414   0.15166  -0.0921   0.0035   1.0000
  18.250   1.2566   0.16387   0.16152  -0.0981   0.0035   1.0000
  18.500   1.2382   0.17442   0.17220  -0.1046   0.0036   1.0000
  18.750   1.2164   0.18663   0.18456  -0.1120   0.0037   1.0000
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