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RAF 32 MOD AIRFOIL (raf32md-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RAF 32 MOD AIRFOIL (raf32md-il)
Reynolds number: 50,000
Max Cl/Cd: 37.5 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf32md-il-50000-n5.txt
Download as CSV file: xf-raf32md-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 32 MOD AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3856   0.10142   0.09453  -0.0448   1.0000   0.0659
  -8.750  -0.3905   0.09863   0.09183  -0.0439   1.0000   0.0654
  -8.500  -0.3971   0.09600   0.08929  -0.0427   1.0000   0.0648
  -8.250  -0.4068   0.09347   0.08687  -0.0413   1.0000   0.0641
  -8.000  -0.4197   0.09113   0.08464  -0.0396   1.0000   0.0635
  -7.750  -0.4340   0.08874   0.08237  -0.0380   1.0000   0.0629
  -7.500  -0.4456   0.08570   0.07943  -0.0377   1.0000   0.0623
  -7.250  -0.4560   0.08217   0.07597  -0.0382   1.0000   0.0616
  -7.000  -0.4647   0.07797   0.07182  -0.0398   1.0000   0.0610
  -6.750  -0.4707   0.07300   0.06686  -0.0424   1.0000   0.0603
  -6.500  -0.4732   0.06758   0.06137  -0.0455   1.0000   0.0603
  -6.250  -0.4713   0.06221   0.05583  -0.0486   1.0000   0.0609
  -6.000  -0.4567   0.05588   0.04911  -0.0544   0.9975   0.0626
  -5.750  -0.4282   0.04895   0.04149  -0.0617   0.9922   0.0641
  -5.500  -0.3970   0.04346   0.03522  -0.0668   0.9874   0.0651
  -5.250  -0.3661   0.03982   0.03094  -0.0700   0.9826   0.0684
  -5.000  -0.3345   0.03791   0.02878  -0.0723   0.9779   0.0723
  -4.750  -0.3031   0.03541   0.02569  -0.0741   0.9730   0.0746
  -4.500  -0.2692   0.03331   0.02303  -0.0759   0.9686   0.0773
  -4.250  -0.2384   0.03193   0.02133  -0.0772   0.9633   0.0823
  -4.000  -0.2055   0.03090   0.02009  -0.0786   0.9583   0.0883
  -3.750  -0.1749   0.02979   0.01861  -0.0792   0.9529   0.0929
  -3.500  -0.1427   0.02884   0.01759  -0.0804   0.9477   0.0985
  -3.250  -0.1122   0.02809   0.01662  -0.0811   0.9419   0.1076
  -3.000  -0.0801   0.02734   0.01581  -0.0822   0.9364   0.1246
  -2.750  -0.0475   0.02654   0.01517  -0.0838   0.9310   0.1645
  -2.500  -0.0164   0.02594   0.01487  -0.0851   0.9247   0.2333
  -2.250   0.0172   0.02564   0.01488  -0.0867   0.9194   0.3412
  -2.000   0.0429   0.02533   0.01486  -0.0867   0.9121   0.4256
  -1.750   0.0759   0.02510   0.01489  -0.0876   0.9071   0.5045
  -1.500   0.0984   0.02502   0.01491  -0.0865   0.8988   0.5749
  -1.250   0.1291   0.02480   0.01483  -0.0867   0.8934   0.6581
  -1.000   0.1486   0.02446   0.01481  -0.0845   0.8856   0.7622
  -0.750   0.1933   0.02410   0.01450  -0.0876   0.8798   1.0000
  -0.500   0.2233   0.02437   0.01447  -0.0885   0.8723   1.0000
  -0.250   0.2559   0.02461   0.01445  -0.0898   0.8654   1.0000
   0.000   0.2855   0.02490   0.01450  -0.0905   0.8581   1.0000
   0.250   0.3162   0.02516   0.01458  -0.0914   0.8508   1.0000
   0.500   0.3456   0.02545   0.01471  -0.0920   0.8435   1.0000
   0.750   0.3751   0.02573   0.01485  -0.0926   0.8360   1.0000
   1.000   0.4043   0.02602   0.01503  -0.0931   0.8287   1.0000
   1.250   0.4329   0.02631   0.01523  -0.0934   0.8210   1.0000
   1.500   0.4619   0.02660   0.01545  -0.0939   0.8137   1.0000
   1.750   0.4898   0.02691   0.01570  -0.0941   0.8058   1.0000
   2.000   0.5178   0.02721   0.01599  -0.0943   0.7982   1.0000
   2.250   0.5462   0.02750   0.01626  -0.0945   0.7905   1.0000
   2.500   0.5716   0.02787   0.01663  -0.0943   0.7820   1.0000
   2.750   0.6024   0.02809   0.01687  -0.0948   0.7750   1.0000
   3.000   0.6246   0.02855   0.01737  -0.0940   0.7655   1.0000
   3.250   0.6586   0.02866   0.01752  -0.0949   0.7592   1.0000
   3.500   0.6779   0.02921   0.01815  -0.0938   0.7488   1.0000
   3.750   0.7154   0.02919   0.01821  -0.0951   0.7434   1.0000
   4.000   0.7325   0.02980   0.01890  -0.0936   0.7320   1.0000
   4.250   0.7580   0.03015   0.01938  -0.0932   0.7231   1.0000
   4.500   0.7892   0.03026   0.01963  -0.0934   0.7152   1.0000
   4.750   0.8085   0.03080   0.02028  -0.0922   0.7040   1.0000
   5.000   0.8488   0.03051   0.02020  -0.0935   0.6982   1.0000
   5.250   0.8667   0.03105   0.02089  -0.0919   0.6857   1.0000
   5.500   0.8883   0.03140   0.02141  -0.0907   0.6736   1.0000
   5.750   0.9164   0.03129   0.02149  -0.0899   0.6609   1.0000
   6.000   0.9466   0.03087   0.02130  -0.0891   0.6462   1.0000
   6.250   0.9757   0.03045   0.02110  -0.0881   0.6300   1.0000
   6.500   1.0048   0.02997   0.02084  -0.0869   0.6124   1.0000
   6.750   1.0289   0.02924   0.02025  -0.0845   0.5851   1.0000
   7.000   1.0515   0.02837   0.01947  -0.0815   0.5480   1.0000
   7.250   1.0608   0.02853   0.01969  -0.0777   0.5109   1.0000
   7.500   1.0754   0.02868   0.01987  -0.0747   0.4724   1.0000
   7.750   1.0842   0.02921   0.02037  -0.0712   0.4237   1.0000
   8.000   1.0910   0.03003   0.02095  -0.0676   0.3593   1.0000
   8.250   1.0899   0.03159   0.02202  -0.0636   0.2845   1.0000
   8.500   1.0842   0.03381   0.02379  -0.0598   0.2238   1.0000
   8.750   1.0803   0.03623   0.02586  -0.0568   0.1831   1.0000
   9.000   1.0789   0.03866   0.02807  -0.0542   0.1544   1.0000
   9.250   1.0793   0.04106   0.03029  -0.0519   0.1335   1.0000
   9.500   1.0835   0.04324   0.03243  -0.0500   0.1162   1.0000
   9.750   1.0884   0.04543   0.03459  -0.0484   0.1013   1.0000
  10.000   1.0944   0.04761   0.03676  -0.0468   0.0898   1.0000
  10.250   1.1019   0.04979   0.03893  -0.0453   0.0797   1.0000
  10.500   1.1173   0.05167   0.04099  -0.0438   0.0703   1.0000
  10.750   1.1362   0.05361   0.04298  -0.0426   0.0626   1.0000
  11.000   1.1608   0.05557   0.04526  -0.0415   0.0560   1.0000
  11.250   1.1818   0.05795   0.04756  -0.0409   0.0507   1.0000
  11.500   1.2000   0.06080   0.05087  -0.0398   0.0477   1.0000
  11.750   1.2107   0.06397   0.05442  -0.0386   0.0453   1.0000
  12.000   1.2139   0.06714   0.05788  -0.0374   0.0433   1.0000
  12.250   1.2144   0.07028   0.06122  -0.0364   0.0416   1.0000
  12.500   1.2158   0.07362   0.06467  -0.0357   0.0400   1.0000
  12.750   1.2094   0.07779   0.06909  -0.0349   0.0392   1.0000
  13.000   1.1959   0.08238   0.07403  -0.0345   0.0389   1.0000
  13.250   1.1803   0.08741   0.07939  -0.0347   0.0387   1.0000
  13.500   1.1631   0.09284   0.08511  -0.0357   0.0386   1.0000
  13.750   1.1444   0.09876   0.09128  -0.0374   0.0386   1.0000
  14.000   1.1245   0.10520   0.09794  -0.0399   0.0387   1.0000
  14.250   1.1040   0.11224   0.10518  -0.0433   0.0388   1.0000
  14.500   1.0838   0.11993   0.11303  -0.0476   0.0390   1.0000
  14.750   1.0643   0.12825   0.12147  -0.0526   0.0392   1.0000
  15.000   1.0467   0.13707   0.13038  -0.0580   0.0395   1.0000
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