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cr001sm (cr001sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: cr001sm (cr001sm-il)
Reynolds number: 200,000
Max Cl/Cd: 83.25 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cr001sm-il-200000-n5.txt
Download as CSV file: xf-cr001sm-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3622   0.09516   0.09177  -0.0294   1.0000   0.0212
  -7.500  -0.3707   0.09334   0.09002  -0.0276   1.0000   0.0212
  -7.250  -0.3768   0.09126   0.08800  -0.0264   1.0000   0.0212
  -7.000  -0.3660   0.08737   0.08414  -0.0301   0.9979   0.0212
  -6.750  -0.3427   0.08218   0.07892  -0.0375   0.9934   0.0213
  -6.500  -0.3182   0.07692   0.07363  -0.0450   0.9885   0.0213
  -6.250  -0.2905   0.07143   0.06809  -0.0531   0.9845   0.0213
  -6.000  -0.2738   0.06480   0.06146  -0.0593   0.9784   0.0218
  -5.750  -0.2475   0.05995   0.05656  -0.0653   0.9744   0.0223
  -5.500  -0.2258   0.05776   0.05436  -0.0673   0.9705   0.0243
  -5.250  -0.1725   0.05149   0.04775  -0.0811   0.9640   0.0303
  -5.000  -0.1455   0.04306   0.03917  -0.0871   0.9604   0.0203
  -4.750  -0.1163   0.03822   0.03411  -0.0916   0.9547   0.0190
  -4.500  -0.0809   0.03259   0.02807  -0.0965   0.9499   0.0178
  -4.250  -0.0425   0.02719   0.02208  -0.1006   0.9470   0.0169
  -4.000  -0.0090   0.02338   0.01768  -0.1027   0.9427   0.0167
  -3.750   0.0222   0.02080   0.01461  -0.1036   0.9374   0.0170
  -3.500   0.0573   0.01874   0.01211  -0.1052   0.9342   0.0178
  -3.250   0.0942   0.01743   0.01045  -0.1069   0.9317   0.0200
  -3.000   0.1219   0.01666   0.00940  -0.1066   0.9242   0.0213
  -2.750   0.1551   0.01492   0.00746  -0.1077   0.9202   0.0224
  -2.500   0.1865   0.01399   0.00648  -0.1083   0.9148   0.0239
  -2.250   0.2171   0.01336   0.00579  -0.1088   0.9081   0.0265
  -2.000   0.2519   0.01283   0.00518  -0.1100   0.9035   0.0299
  -1.750   0.2798   0.01219   0.00448  -0.1100   0.8947   0.0325
  -1.500   0.3133   0.01173   0.00396  -0.1110   0.8886   0.0373
  -1.250   0.3430   0.01138   0.00358  -0.1112   0.8796   0.0480
  -1.000   0.3735   0.01085   0.00325  -0.1117   0.8710   0.1114
  -0.750   0.4041   0.01014   0.00311  -0.1126   0.8626   0.3041
  -0.500   0.4278   0.00927   0.00319  -0.1118   0.8517   0.5913
  -0.250   0.4669   0.00837   0.00303  -0.1135   0.8428   1.0000
   0.000   0.4969   0.00838   0.00288  -0.1137   0.8312   1.0000
   0.250   0.5263   0.00842   0.00277  -0.1138   0.8189   1.0000
   0.500   0.5550   0.00846   0.00269  -0.1137   0.8055   1.0000
   0.750   0.5829   0.00853   0.00264  -0.1135   0.7908   1.0000
   1.000   0.6102   0.00861   0.00261  -0.1132   0.7747   1.0000
   1.250   0.6372   0.00870   0.00259  -0.1128   0.7568   1.0000
   1.500   0.6641   0.00882   0.00257  -0.1123   0.7369   1.0000
   1.750   0.6901   0.00895   0.00261  -0.1117   0.7157   1.0000
   2.000   0.7159   0.00911   0.00264  -0.1111   0.6943   1.0000
   2.250   0.7412   0.00928   0.00270  -0.1104   0.6727   1.0000
   2.500   0.7664   0.00948   0.00278  -0.1097   0.6510   1.0000
   2.750   0.7912   0.00968   0.00292  -0.1089   0.6289   1.0000
   3.000   0.8158   0.00991   0.00304  -0.1081   0.6067   1.0000
   3.250   0.8401   0.01014   0.00319  -0.1073   0.5840   1.0000
   3.500   0.8643   0.01039   0.00336  -0.1065   0.5613   1.0000
   4.000   0.9116   0.01095   0.00379  -0.1047   0.5131   1.0000
   4.250   0.9349   0.01127   0.00402  -0.1037   0.4872   1.0000
   4.500   0.9577   0.01160   0.00428  -0.1027   0.4604   1.0000
   4.750   0.9802   0.01197   0.00456  -0.1017   0.4318   1.0000
   5.000   1.0021   0.01238   0.00490  -0.1005   0.4003   1.0000
   5.250   1.0234   0.01284   0.00524  -0.0993   0.3667   1.0000
   5.500   1.0444   0.01334   0.00562  -0.0981   0.3314   1.0000
   5.750   1.0648   0.01390   0.00604  -0.0969   0.2965   1.0000
   6.000   1.0853   0.01447   0.00650  -0.0957   0.2634   1.0000
   6.250   1.1057   0.01507   0.00702  -0.0945   0.2336   1.0000
   6.500   1.1259   0.01569   0.00755  -0.0933   0.2057   1.0000
   6.750   1.1459   0.01632   0.00810  -0.0921   0.1796   1.0000
   7.000   1.1656   0.01699   0.00869  -0.0908   0.1536   1.0000
   7.250   1.1848   0.01771   0.00931  -0.0895   0.1269   1.0000
   7.500   1.2033   0.01848   0.01001  -0.0882   0.1012   1.0000
   7.750   1.2210   0.01933   0.01075  -0.0867   0.0777   1.0000
   8.000   1.2380   0.02024   0.01158  -0.0851   0.0581   1.0000
   8.250   1.2543   0.02120   0.01249  -0.0834   0.0433   1.0000
   8.500   1.2697   0.02221   0.01350  -0.0816   0.0340   1.0000
   8.750   1.2856   0.02314   0.01454  -0.0797   0.0285   1.0000
   9.000   1.2981   0.02432   0.01580  -0.0775   0.0244   1.0000
   9.250   1.3122   0.02524   0.01687  -0.0754   0.0214   1.0000
   9.500   1.3228   0.02634   0.01806  -0.0729   0.0191   1.0000
   9.750   1.3272   0.02786   0.01969  -0.0695   0.0175   1.0000
  10.000   1.3358   0.02908   0.02106  -0.0669   0.0166   1.0000
  10.250   1.3441   0.03034   0.02248  -0.0643   0.0154   1.0000
  10.500   1.3522   0.03162   0.02389  -0.0619   0.0142   1.0000
  10.750   1.3590   0.03301   0.02539  -0.0596   0.0132   1.0000
  11.000   1.3616   0.03481   0.02730  -0.0570   0.0124   1.0000
  11.250   1.3592   0.03725   0.02987  -0.0542   0.0119   1.0000
  11.500   1.3634   0.03916   0.03199  -0.0521   0.0115   1.0000
  11.750   1.3662   0.04132   0.03436  -0.0501   0.0111   1.0000
  12.000   1.3679   0.04370   0.03693  -0.0483   0.0107   1.0000
  12.250   1.3682   0.04629   0.03973  -0.0467   0.0104   1.0000
  12.500   1.3676   0.04904   0.04269  -0.0454   0.0100   1.0000
  12.750   1.3660   0.05191   0.04574  -0.0444   0.0096   1.0000
  13.000   1.3632   0.05497   0.04900  -0.0437   0.0093   1.0000
  13.250   1.3592   0.05829   0.05249  -0.0434   0.0090   1.0000
  13.500   1.3541   0.06189   0.05626  -0.0436   0.0088   1.0000
  13.750   1.3480   0.06574   0.06025  -0.0442   0.0085   1.0000
  14.000   1.3390   0.07034   0.06503  -0.0451   0.0083   1.0000
  14.250   1.3287   0.07535   0.07021  -0.0465   0.0082   1.0000
  14.500   1.3165   0.08096   0.07601  -0.0485   0.0081   1.0000
  14.750   1.3022   0.08728   0.08252  -0.0512   0.0080   1.0000
  15.250   1.2734   0.10106   0.09670  -0.0580   0.0079   1.0000
  15.500   1.2582   0.10872   0.10455  -0.0624   0.0079   1.0000
  15.750   1.2432   0.11670   0.11272  -0.0671   0.0079   1.0000
  16.000   1.2275   0.12525   0.12144  -0.0723   0.0079   1.0000
  16.500   1.1969   0.14364   0.14018  -0.0839   0.0080   1.0000
  16.750   1.0910   0.18878   0.18565  -0.1098   0.0105   1.0000
  17.000   1.0824   0.19942   0.19623  -0.1151   0.0104   1.0000
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