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cr001sm (cr001sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: cr001sm (cr001sm-il)
Reynolds number: 50,000
Max Cl/Cd: 44.23 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cr001sm-il-50000-n5.txt
Download as CSV file: xf-cr001sm-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3565   0.11054   0.10353  -0.0295   1.0000   0.0949
  -8.250  -0.3672   0.10984   0.10298  -0.0306   1.0000   0.0963
  -8.000  -0.3802   0.10911   0.10241  -0.0310   1.0000   0.0967
  -7.750  -0.3579   0.10266   0.09590  -0.0288   1.0000   0.0994
  -7.500  -0.3542   0.09980   0.09310  -0.0276   1.0000   0.1024
  -7.250  -0.3575   0.09776   0.09116  -0.0266   1.0000   0.1051
  -7.000  -0.3656   0.09620   0.08974  -0.0265   1.0000   0.1085
  -6.750  -0.3781   0.09542   0.08911  -0.0318   1.0000   0.1108
  -6.500  -0.3718   0.09124   0.08501  -0.0285   1.0000   0.1124
  -6.250  -0.3668   0.08815   0.08197  -0.0263   1.0000   0.1150
  -6.000  -0.3647   0.08553   0.07940  -0.0260   1.0000   0.1183
  -5.750  -0.3642   0.08345   0.07736  -0.0352   1.0000   0.1253
  -5.250  -0.3536   0.07743   0.07143  -0.0320   1.0000   0.1382
  -4.750  -0.3061   0.06426   0.05784  -0.0461   1.0000   0.0680
  -4.500  -0.2958   0.06106   0.05467  -0.0455   1.0000   0.0656
  -4.250  -0.2563   0.05396   0.04696  -0.0553   1.0000   0.0554
  -4.000  -0.2412   0.05084   0.04383  -0.0552   1.0000   0.0538
  -3.750  -0.2188   0.04722   0.04002  -0.0571   1.0000   0.0523
  -3.500  -0.1917   0.04347   0.03592  -0.0598   1.0000   0.0508
  -3.250  -0.1620   0.03988   0.03189  -0.0624   1.0000   0.0496
  -3.000  -0.1315   0.03667   0.02817  -0.0646   1.0000   0.0490
  -2.750  -0.1017   0.03410   0.02507  -0.0660   1.0000   0.0499
  -2.500  -0.0632   0.03182   0.02211  -0.0686   0.9966   0.0533
  -2.250  -0.0227   0.02983   0.01944  -0.0711   0.9915   0.0550
  -2.000   0.0157   0.02796   0.01721  -0.0733   0.9863   0.0568
  -1.750   0.0516   0.02669   0.01571  -0.0750   0.9799   0.0607
  -1.500   0.0899   0.02586   0.01452  -0.0768   0.9736   0.0691
  -1.250   0.1259   0.02493   0.01344  -0.0785   0.9665   0.0761
  -1.000   0.1663   0.02422   0.01253  -0.0809   0.9600   0.0906
  -0.750   0.2033   0.02342   0.01184  -0.0829   0.9519   0.1306
  -0.500   0.2365   0.02099   0.01179  -0.0840   0.9474   0.6862
  -0.250   0.2717   0.02067   0.01133  -0.0852   0.9358   1.0000
   0.000   0.3075   0.02092   0.01117  -0.0869   0.9257   1.0000
   0.250   0.3467   0.02115   0.01107  -0.0892   0.9169   1.0000
   0.500   0.3808   0.02135   0.01104  -0.0906   0.9060   1.0000
   0.750   0.4140   0.02156   0.01103  -0.0917   0.8947   1.0000
   1.000   0.4485   0.02173   0.01105  -0.0930   0.8838   1.0000
   1.250   0.4862   0.02184   0.01104  -0.0948   0.8741   1.0000
   1.500   0.5218   0.02194   0.01106  -0.0961   0.8633   1.0000
   2.000   0.5872   0.02217   0.01119  -0.0976   0.8388   1.0000
   2.250   0.6200   0.02224   0.01124  -0.0983   0.8264   1.0000
   2.500   0.6529   0.02228   0.01131  -0.0988   0.8136   1.0000
   2.750   0.6854   0.02230   0.01135  -0.0992   0.8002   1.0000
   3.000   0.7174   0.02229   0.01138  -0.0995   0.7858   1.0000
   3.250   0.7490   0.02226   0.01144  -0.0995   0.7702   1.0000
   3.500   0.7807   0.02218   0.01142  -0.0995   0.7538   1.0000
   3.750   0.8132   0.02206   0.01136  -0.0994   0.7366   1.0000
   4.000   0.8409   0.02210   0.01147  -0.0987   0.7165   1.0000
   4.250   0.8703   0.02208   0.01158  -0.0981   0.6961   1.0000
   4.500   0.8978   0.02215   0.01172  -0.0973   0.6740   1.0000
   4.750   0.9264   0.02219   0.01182  -0.0966   0.6512   1.0000
   5.000   0.9514   0.02238   0.01210  -0.0954   0.6257   1.0000
   5.250   0.9764   0.02261   0.01238  -0.0942   0.5989   1.0000
   5.500   1.0006   0.02288   0.01278  -0.0929   0.5706   1.0000
   5.750   1.0238   0.02323   0.01316  -0.0915   0.5403   1.0000
   6.000   1.0460   0.02365   0.01359  -0.0899   0.5086   1.0000
   6.250   1.0659   0.02418   0.01417  -0.0881   0.4742   1.0000
   6.500   1.0853   0.02479   0.01481  -0.0863   0.4390   1.0000
   6.750   1.1029   0.02552   0.01554  -0.0843   0.4021   1.0000
   7.000   1.1196   0.02635   0.01632  -0.0823   0.3658   1.0000
   7.250   1.1349   0.02730   0.01723  -0.0802   0.3295   1.0000
   7.500   1.1491   0.02838   0.01824  -0.0781   0.2950   1.0000
   7.750   1.1623   0.02956   0.01938  -0.0759   0.2615   1.0000
   8.000   1.1739   0.03088   0.02069  -0.0737   0.2299   1.0000
   8.250   1.1839   0.03231   0.02205  -0.0714   0.1999   1.0000
   8.500   1.1931   0.03386   0.02357  -0.0691   0.1707   1.0000
   8.750   1.2003   0.03556   0.02522  -0.0667   0.1443   1.0000
   9.000   1.2063   0.03735   0.02702  -0.0642   0.1207   1.0000
   9.250   1.2119   0.03936   0.02900  -0.0616   0.1026   1.0000
   9.500   1.2174   0.04144   0.03113  -0.0593   0.0872   1.0000
   9.750   1.2237   0.04370   0.03343  -0.0570   0.0768   1.0000
  10.000   1.2286   0.04595   0.03572  -0.0550   0.0684   1.0000
  10.250   1.2371   0.04833   0.03843  -0.0531   0.0606   1.0000
  10.500   1.2449   0.05091   0.04100  -0.0514   0.0561   1.0000
  10.750   1.2558   0.05377   0.04428  -0.0498   0.0513   1.0000
  11.000   1.2590   0.05645   0.04717  -0.0481   0.0475   1.0000
  11.250   1.2628   0.05937   0.05004  -0.0469   0.0446   1.0000
  11.500   1.2648   0.06301   0.05418  -0.0454   0.0429   1.0000
  11.750   1.2619   0.06704   0.05864  -0.0441   0.0417   1.0000
  12.000   1.2543   0.07136   0.06332  -0.0432   0.0410   1.0000
  12.250   1.2426   0.07610   0.06840  -0.0430   0.0404   1.0000
  12.500   1.2274   0.08134   0.07394  -0.0435   0.0401   1.0000
  12.750   1.2095   0.08721   0.08009  -0.0451   0.0401   1.0000
  13.000   1.1891   0.09389   0.08702  -0.0478   0.0402   1.0000
  13.250   1.1668   0.10149   0.09483  -0.0517   0.0405   1.0000
  13.500   1.1434   0.11011   0.10363  -0.0569   0.0410   1.0000
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