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cr001sm (cr001sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: cr001sm (cr001sm-il)
Reynolds number: 200,000
Max Cl/Cd: 89.27 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cr001sm-il-200000.txt
Download as CSV file: xf-cr001sm-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3624   0.10032   0.09693  -0.0309   1.0000   0.0302
  -7.750  -0.3698   0.09862   0.09529  -0.0294   1.0000   0.0303
  -7.500  -0.3767   0.09675   0.09350  -0.0284   1.0000   0.0303
  -7.250  -0.3793   0.09437   0.09117  -0.0285   1.0000   0.0304
  -7.000  -0.3809   0.09186   0.08870  -0.0291   1.0000   0.0304
  -6.750  -0.3890   0.08672   0.08364  -0.0275   1.0000   0.0310
  -6.500  -0.3906   0.08391   0.08084  -0.0241   1.0000   0.0317
  -6.250  -0.3911   0.08151   0.07848  -0.0229   1.0000   0.0321
  -6.000  -0.3909   0.07918   0.07618  -0.0219   1.0000   0.0329
  -5.750  -0.3895   0.07669   0.07372  -0.0218   1.0000   0.0337
  -5.500  -0.3858   0.07395   0.07099  -0.0229   1.0000   0.0346
  -5.250  -0.3561   0.06919   0.06619  -0.0307   0.9967   0.0369
  -5.000  -0.2882   0.06148   0.05819  -0.0517   0.9911   0.0416
  -4.750  -0.2534   0.05359   0.05014  -0.0608   0.9870   0.0433
  -4.500  -0.2332   0.05172   0.04836  -0.0609   0.9829   0.0465
  -4.250  -0.1908   0.04703   0.04345  -0.0686   0.9778   0.0523
  -4.000  -0.1423   0.04068   0.03667  -0.0778   0.9744   0.0575
  -3.750  -0.1094   0.03808   0.03401  -0.0808   0.9703   0.0619
  -3.500  -0.0684   0.03397   0.02945  -0.0859   0.9650   0.0716
  -3.250  -0.0265   0.03130   0.02639  -0.0902   0.9615   0.0846
  -3.000   0.0140   0.02884   0.02374  -0.0940   0.9592   0.0991
  -2.750   0.0424   0.02692   0.02171  -0.0950   0.9518   0.1141
  -2.500   0.0930   0.02067   0.01414  -0.0958   0.9502   0.0477
  -2.250   0.1348   0.01859   0.01151  -0.0976   0.9475   0.0444
  -2.000   0.1748   0.01715   0.00983  -0.0995   0.9444   0.0442
  -1.750   0.2060   0.01607   0.00870  -0.0999   0.9373   0.0464
  -1.500   0.2466   0.01528   0.00787  -0.1022   0.9337   0.0531
  -1.000   0.3189   0.01367   0.00628  -0.1050   0.9226   0.0730
  -0.750   0.3560   0.01166   0.00593  -0.1074   0.9197   0.5356
  -0.500   0.4061   0.01042   0.00558  -0.1112   0.9185   1.0000
  -0.250   0.4378   0.01033   0.00533  -0.1117   0.9094   1.0000
   0.000   0.4796   0.01010   0.00496  -0.1141   0.9049   1.0000
   0.250   0.5105   0.01000   0.00476  -0.1144   0.8950   1.0000
   0.500   0.5472   0.00982   0.00448  -0.1158   0.8877   1.0000
   0.750   0.5801   0.00968   0.00426  -0.1164   0.8778   1.0000
   1.000   0.6104   0.00958   0.00410  -0.1165   0.8659   1.0000
   1.250   0.6408   0.00949   0.00394  -0.1165   0.8529   1.0000
   1.500   0.6705   0.00941   0.00379  -0.1164   0.8385   1.0000
   1.750   0.6995   0.00936   0.00369  -0.1161   0.8229   1.0000
   2.000   0.7281   0.00936   0.00361  -0.1158   0.8067   1.0000
   2.250   0.7546   0.00941   0.00360  -0.1151   0.7886   1.0000
   2.500   0.7807   0.00948   0.00361  -0.1144   0.7696   1.0000
   2.750   0.8075   0.00958   0.00365  -0.1138   0.7509   1.0000
   3.000   0.8328   0.00971   0.00372  -0.1130   0.7304   1.0000
   3.250   0.8582   0.00986   0.00380  -0.1122   0.7097   1.0000
   3.500   0.8830   0.01003   0.00392  -0.1113   0.6880   1.0000
   3.750   0.9077   0.01024   0.00404  -0.1104   0.6658   1.0000
   4.000   0.9315   0.01045   0.00424  -0.1094   0.6419   1.0000
   4.250   0.9552   0.01070   0.00443  -0.1083   0.6176   1.0000
   4.500   0.9784   0.01097   0.00463  -0.1072   0.5921   1.0000
   4.750   1.0011   0.01127   0.00485  -0.1060   0.5651   1.0000
   5.000   1.0232   0.01160   0.00514  -0.1047   0.5358   1.0000
   5.250   1.0447   0.01195   0.00542  -0.1033   0.5038   1.0000
   5.500   1.0654   0.01236   0.00574  -0.1018   0.4694   1.0000
   5.750   1.0854   0.01282   0.00609  -0.1003   0.4317   1.0000
   6.000   1.1046   0.01335   0.00648  -0.0986   0.3905   1.0000
   6.250   1.1229   0.01397   0.00696  -0.0969   0.3470   1.0000
   6.500   1.1408   0.01466   0.00748  -0.0952   0.3046   1.0000
   6.750   1.1585   0.01541   0.00806  -0.0935   0.2665   1.0000
   7.000   1.1765   0.01616   0.00867  -0.0919   0.2313   1.0000
   7.250   1.1941   0.01695   0.00933  -0.0903   0.1989   1.0000
   7.500   1.2121   0.01772   0.01003  -0.0888   0.1668   1.0000
   7.750   1.2287   0.01863   0.01079  -0.0872   0.1330   1.0000
   8.000   1.2431   0.01977   0.01173  -0.0852   0.0953   1.0000
   8.250   1.2537   0.02130   0.01305  -0.0825   0.0658   1.0000
   8.500   1.2641   0.02281   0.01455  -0.0797   0.0510   1.0000
   8.750   1.2718   0.02452   0.01625  -0.0766   0.0434   1.0000
   9.000   1.2847   0.02565   0.01748  -0.0743   0.0377   1.0000
   9.250   1.2889   0.02781   0.01966  -0.0709   0.0340   1.0000
   9.500   1.3023   0.02918   0.02121  -0.0686   0.0318   1.0000
   9.750   1.3150   0.03071   0.02288  -0.0664   0.0294   1.0000
  10.000   1.3257   0.03224   0.02444  -0.0642   0.0270   1.0000
  10.250   1.3417   0.03570   0.02805  -0.0631   0.0247   1.0000
  10.500   1.3551   0.03767   0.03028  -0.0612   0.0238   1.0000
  10.750   1.3670   0.04015   0.03306  -0.0591   0.0230   1.0000
  11.000   1.3748   0.04295   0.03617  -0.0568   0.0223   1.0000
  11.250   1.3777   0.04578   0.03931  -0.0540   0.0218   1.0000
  11.500   1.3764   0.04852   0.04234  -0.0511   0.0213   1.0000
  11.750   1.3733   0.05093   0.04499  -0.0484   0.0205   1.0000
  12.000   1.3690   0.05353   0.04779  -0.0460   0.0199   1.0000
  12.250   1.3608   0.05662   0.05110  -0.0438   0.0195   1.0000
  12.500   1.3516   0.05984   0.05451  -0.0422   0.0191   1.0000
  12.750   1.3391   0.06377   0.05868  -0.0410   0.0189   1.0000
  13.000   1.3224   0.06845   0.06364  -0.0404   0.0190   1.0000
  13.250   1.3030   0.07381   0.06928  -0.0408   0.0192   1.0000
  13.500   1.2812   0.07992   0.07566  -0.0422   0.0194   1.0000
  13.750   1.2555   0.08708   0.08310  -0.0451   0.0196   1.0000
  14.000   1.2233   0.09629   0.09260  -0.0502   0.0202   1.0000
  14.250   1.1874   0.10772   0.10427  -0.0574   0.0211   1.0000
  14.500   1.1539   0.12031   0.11705  -0.0659   0.0224   1.0000
  14.750   1.1253   0.13305   0.12990  -0.0743   0.0236   1.0000
  15.000   1.1013   0.14538   0.14225  -0.0818   0.0246   1.0000
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