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cr001sm (cr001sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: cr001sm (cr001sm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 119.68 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cr001sm-il-1000000-n5.txt
Download as CSV file: xf-cr001sm-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.2999   0.13314   0.13150  -0.0267   1.0000   0.0052
 -12.250  -0.2970   0.13042   0.12879  -0.0270   1.0000   0.0055
 -11.750  -0.4016   0.13456   0.13278  -0.0201   1.0000   0.0046
 -11.500  -0.3957   0.13202   0.13025  -0.0208   1.0000   0.0050
 -11.250  -0.3942   0.12745   0.12569  -0.0218   1.0000   0.0045
  -9.750  -0.3695   0.10989   0.10821  -0.0254   1.0000   0.0066
  -9.500  -0.3676   0.10695   0.10528  -0.0258   1.0000   0.0066
  -9.250  -0.3663   0.10408   0.10242  -0.0258   1.0000   0.0066
  -8.750  -0.3501   0.09760   0.09597  -0.0295   0.9990   0.0060
  -8.500  -0.3364   0.09289   0.09126  -0.0346   0.9974   0.0067
  -8.000  -0.3149   0.08574   0.08412  -0.0401   0.9927   0.0061
  -7.750  -0.3028   0.08188   0.08026  -0.0440   0.9892   0.0059
  -7.500  -0.2892   0.07759   0.07598  -0.0489   0.9856   0.0057
  -7.250  -0.2779   0.07350   0.07188  -0.0533   0.9791   0.0054
  -7.000  -0.2575   0.06804   0.06642  -0.0613   0.9750   0.0053
  -6.750  -0.2329   0.06167   0.06003  -0.0714   0.9704   0.0051
  -6.500  -0.2045   0.05483   0.05314  -0.0826   0.9635   0.0052
  -6.250  -0.1598   0.04487   0.04304  -0.0999   0.9597   0.0052
  -6.000  -0.1226   0.03349   0.03134  -0.1131   0.9503   0.0057
  -5.750  -0.1016   0.01324   0.00929  -0.1208   0.9371   0.0064
  -5.500  -0.0719   0.01198   0.00775  -0.1216   0.9308   0.0066
  -5.250  -0.0440   0.01134   0.00695  -0.1217   0.9225   0.0067
  -5.000  -0.0169   0.00993   0.00524  -0.1218   0.9141   0.0072
  -4.750   0.0111   0.00938   0.00457  -0.1219   0.9051   0.0075
  -4.500   0.0385   0.00904   0.00415  -0.1218   0.8954   0.0078
  -4.250   0.0660   0.00874   0.00376  -0.1217   0.8855   0.0083
  -4.000   0.0931   0.00845   0.00337  -0.1215   0.8752   0.0089
  -3.750   0.1198   0.00817   0.00300  -0.1212   0.8641   0.0094
  -3.500   0.1465   0.00796   0.00270  -0.1208   0.8530   0.0099
  -3.250   0.1728   0.00765   0.00230  -0.1204   0.8417   0.0105
  -3.000   0.1992   0.00747   0.00205  -0.1200   0.8298   0.0114
  -2.750   0.2256   0.00737   0.00189  -0.1196   0.8172   0.0124
  -2.500   0.2520   0.00729   0.00175  -0.1192   0.8044   0.0137
  -2.250   0.2782   0.00723   0.00161  -0.1188   0.7908   0.0144
  -2.000   0.3043   0.00707   0.00136  -0.1183   0.7768   0.0155
  -1.750   0.3304   0.00696   0.00118  -0.1178   0.7623   0.0173
  -1.500   0.3566   0.00692   0.00108  -0.1174   0.7476   0.0193
  -1.250   0.3827   0.00690   0.00099  -0.1169   0.7323   0.0208
  -1.000   0.4088   0.00688   0.00089  -0.1164   0.7159   0.0239
  -0.750   0.4346   0.00687   0.00084  -0.1159   0.6980   0.0325
  -0.500   0.4598   0.00679   0.00080  -0.1153   0.6782   0.0774
  -0.250   0.4848   0.00668   0.00079  -0.1147   0.6546   0.1504
   0.000   0.5097   0.00662   0.00080  -0.1142   0.6307   0.2209
   0.250   0.5343   0.00650   0.00085  -0.1136   0.6077   0.3247
   0.500   0.5591   0.00637   0.00092  -0.1131   0.5863   0.4324
   0.750   0.5832   0.00619   0.00102  -0.1124   0.5663   0.5726
   1.000   0.6072   0.00608   0.00110  -0.1116   0.5457   0.6808
   1.250   0.6282   0.00585   0.00119  -0.1101   0.5266   0.8282
   1.750   0.6926   0.00590   0.00132  -0.1120   0.4849   1.0000
   2.000   0.7182   0.00608   0.00139  -0.1115   0.4656   1.0000
   2.250   0.7439   0.00625   0.00147  -0.1110   0.4458   1.0000
   2.750   0.7947   0.00664   0.00168  -0.1100   0.4030   1.0000
   3.000   0.8198   0.00687   0.00179  -0.1095   0.3797   1.0000
   3.250   0.8447   0.00710   0.00192  -0.1089   0.3554   1.0000
   3.500   0.8693   0.00738   0.00207  -0.1083   0.3276   1.0000
   3.750   0.8936   0.00768   0.00224  -0.1076   0.2988   1.0000
   4.000   0.9179   0.00798   0.00244  -0.1070   0.2716   1.0000
   4.250   0.9420   0.00831   0.00264  -0.1063   0.2443   1.0000
   4.500   0.9663   0.00861   0.00284  -0.1057   0.2218   1.0000
   4.750   0.9905   0.00892   0.00305  -0.1050   0.2006   1.0000
   5.000   1.0146   0.00924   0.00329  -0.1044   0.1791   1.0000
   5.250   1.0384   0.00957   0.00353  -0.1037   0.1595   1.0000
   5.500   1.0623   0.00990   0.00378  -0.1030   0.1400   1.0000
   5.750   1.0848   0.01035   0.00409  -0.1021   0.1132   1.0000
   6.000   1.1074   0.01080   0.00441  -0.1013   0.0910   1.0000
   6.250   1.1306   0.01118   0.00473  -0.1005   0.0754   1.0000
   6.500   1.1535   0.01158   0.00507  -0.0996   0.0608   1.0000
   6.750   1.1761   0.01200   0.00543  -0.0988   0.0483   1.0000
   7.000   1.1985   0.01243   0.00582  -0.0979   0.0375   1.0000
   7.250   1.2205   0.01289   0.00624  -0.0969   0.0279   1.0000
   7.500   1.2427   0.01333   0.00665  -0.0960   0.0212   1.0000
   7.750   1.2647   0.01377   0.00708  -0.0950   0.0163   1.0000
   8.000   1.2862   0.01423   0.00753  -0.0940   0.0130   1.0000
   8.250   1.3082   0.01464   0.00797  -0.0931   0.0110   1.0000
   8.500   1.3297   0.01508   0.00843  -0.0921   0.0097   1.0000
   8.750   1.3501   0.01560   0.00899  -0.0909   0.0081   1.0000
   9.000   1.3712   0.01604   0.00947  -0.0898   0.0075   1.0000
   9.250   1.3919   0.01648   0.00996  -0.0887   0.0069   1.0000
   9.500   1.4117   0.01699   0.01050  -0.0875   0.0063   1.0000
   9.750   1.4306   0.01755   0.01110  -0.0861   0.0056   1.0000
  10.000   1.4481   0.01820   0.01181  -0.0845   0.0050   1.0000
  10.250   1.4667   0.01872   0.01241  -0.0830   0.0048   1.0000
  10.500   1.4843   0.01927   0.01303  -0.0815   0.0045   1.0000
  10.750   1.4995   0.01987   0.01369  -0.0795   0.0042   1.0000
  11.000   1.5136   0.02047   0.01435  -0.0773   0.0039   1.0000
  11.250   1.5264   0.02113   0.01507  -0.0750   0.0037   1.0000
  11.500   1.5381   0.02187   0.01587  -0.0725   0.0034   1.0000
  11.750   1.5467   0.02282   0.01691  -0.0697   0.0031   1.0000
  12.000   1.5549   0.02381   0.01799  -0.0669   0.0030   1.0000
  12.250   1.5641   0.02473   0.01901  -0.0645   0.0029   1.0000
  12.500   1.5734   0.02566   0.02005  -0.0621   0.0028   1.0000
  12.750   1.5812   0.02672   0.02120  -0.0598   0.0027   1.0000
  13.000   1.5877   0.02791   0.02249  -0.0574   0.0026   1.0000
  13.250   1.5928   0.02924   0.02394  -0.0550   0.0026   1.0000
  13.500   1.5973   0.03067   0.02548  -0.0528   0.0025   1.0000
  13.750   1.6011   0.03224   0.02715  -0.0507   0.0024   1.0000
  14.000   1.6024   0.03408   0.02911  -0.0487   0.0024   1.0000
  14.250   1.6045   0.03595   0.03109  -0.0470   0.0023   1.0000
  14.500   1.6045   0.03812   0.03338  -0.0455   0.0022   1.0000
  14.750   1.6063   0.04022   0.03557  -0.0443   0.0021   1.0000
  15.000   1.6031   0.04297   0.03845  -0.0433   0.0021   1.0000
  15.250   1.6029   0.04553   0.04112  -0.0426   0.0020   1.0000
  15.500   1.5962   0.04903   0.04476  -0.0423   0.0020   1.0000
  15.750   1.5929   0.05230   0.04814  -0.0423   0.0020   1.0000
  16.000   1.5851   0.05638   0.05235  -0.0428   0.0019   1.0000
  16.250   1.5753   0.06099   0.05712  -0.0438   0.0019   1.0000
  16.500   1.5662   0.06581   0.06207  -0.0451   0.0019   1.0000
  16.750   1.5519   0.07172   0.06814  -0.0473   0.0019   1.0000
  17.000   1.5358   0.07829   0.07485  -0.0500   0.0018   1.0000
  17.250   1.5201   0.08514   0.08185  -0.0532   0.0018   1.0000
  17.500   1.5017   0.09280   0.08966  -0.0569   0.0018   1.0000
  17.750   1.4813   0.10120   0.09822  -0.0613   0.0018   1.0000
  18.000   1.4575   0.11068   0.10787  -0.0664   0.0018   1.0000
  18.250   1.4349   0.12018   0.11751  -0.0717   0.0018   1.0000
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