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RAF 28 AIRFOIL (raf28-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RAF 28 AIRFOIL (raf28-il)
Reynolds number: 500,000
Max Cl/Cd: 90.59 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf28-il-500000.txt
Download as CSV file: xf-raf28-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 28 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5722   0.07200   0.06974  -0.0381   1.0000   0.0193
  -9.750  -0.6094   0.05746   0.05516  -0.0515   1.0000   0.0186
  -9.500  -0.6404   0.05261   0.05021  -0.0522   1.0000   0.0182
  -9.250  -0.6706   0.04688   0.04427  -0.0504   1.0000   0.0180
  -9.000  -0.6966   0.04075   0.03777  -0.0475   1.0000   0.0178
  -8.750  -0.7114   0.03559   0.03219  -0.0440   1.0000   0.0179
  -8.500  -0.7164   0.03152   0.02769  -0.0405   1.0000   0.0182
  -8.250  -0.7117   0.02888   0.02465  -0.0375   1.0000   0.0190
  -8.000  -0.6964   0.02864   0.02416  -0.0353   1.0000   0.0196
  -7.750  -0.6972   0.02435   0.01954  -0.0320   1.0000   0.0205
  -7.500  -0.6825   0.02347   0.01861  -0.0302   0.9998   0.0212
  -7.250  -0.6486   0.02233   0.01736  -0.0322   0.9971   0.0223
  -7.000  -0.6144   0.02100   0.01581  -0.0341   0.9944   0.0237
  -6.750  -0.5810   0.02011   0.01468  -0.0355   0.9906   0.0251
  -6.500  -0.5499   0.01791   0.01218  -0.0368   0.9868   0.0268
  -6.250  -0.5157   0.01663   0.01084  -0.0387   0.9841   0.0284
  -6.000  -0.4840   0.01578   0.00991  -0.0397   0.9789   0.0299
  -5.750  -0.4499   0.01501   0.00906  -0.0412   0.9745   0.0317
  -5.500  -0.4135   0.01450   0.00846  -0.0430   0.9715   0.0334
  -5.250  -0.3829   0.01367   0.00754  -0.0437   0.9647   0.0343
  -5.000  -0.3517   0.01228   0.00606  -0.0447   0.9597   0.0365
  -4.750  -0.3181   0.01164   0.00540  -0.0460   0.9540   0.0384
  -4.500  -0.2853   0.01109   0.00481  -0.0471   0.9462   0.0400
  -4.250  -0.2513   0.01061   0.00427  -0.0485   0.9384   0.0417
  -4.000  -0.2164   0.01021   0.00381  -0.0500   0.9299   0.0434
  -3.750  -0.1840   0.00979   0.00332  -0.0509   0.9187   0.0450
  -3.500  -0.1524   0.00942   0.00289  -0.0516   0.9070   0.0485
  -3.250  -0.1222   0.00916   0.00259  -0.0520   0.8950   0.0538
  -3.000  -0.0945   0.00882   0.00234  -0.0520   0.8833   0.0826
  -2.750  -0.0702   0.00827   0.00209  -0.0514   0.8716   0.1683
  -2.500  -0.0465   0.00783   0.00197  -0.0507   0.8604   0.2688
  -2.250  -0.0216   0.00757   0.00188  -0.0501   0.8505   0.3326
  -2.000   0.0034   0.00735   0.00180  -0.0496   0.8408   0.3899
  -1.750   0.0274   0.00712   0.00174  -0.0488   0.8306   0.4528
  -1.500   0.0508   0.00686   0.00169  -0.0478   0.8211   0.5261
  -1.250   0.0722   0.00653   0.00168  -0.0464   0.8117   0.6284
  -1.000   0.0928   0.00624   0.00170  -0.0446   0.8015   0.7246
  -0.750   0.1156   0.00605   0.00171  -0.0432   0.7919   0.7937
  -0.500   0.1432   0.00588   0.00175  -0.0427   0.7822   0.8669
  -0.250   0.1956   0.00592   0.00189  -0.0475   0.7720   0.9339
   0.000   0.2391   0.00604   0.00197  -0.0506   0.7613   0.9578
   0.250   0.2758   0.00616   0.00202  -0.0523   0.7498   0.9697
   0.500   0.3177   0.00623   0.00203  -0.0552   0.7362   0.9754
   0.750   0.3535   0.00631   0.00205  -0.0569   0.7195   0.9833
   1.000   0.3944   0.00636   0.00203  -0.0597   0.7028   0.9879
   1.250   0.4326   0.00645   0.00203  -0.0620   0.6837   0.9936
   1.500   0.4726   0.00651   0.00198  -0.0646   0.6615   0.9982
   1.750   0.5023   0.00659   0.00197  -0.0651   0.6420   1.0000
   2.000   0.5244   0.00667   0.00200  -0.0640   0.6263   1.0000
   2.250   0.5467   0.00677   0.00203  -0.0628   0.6102   1.0000
   2.500   0.5691   0.00687   0.00207  -0.0617   0.5934   1.0000
   2.750   0.5913   0.00699   0.00212  -0.0605   0.5748   1.0000
   3.000   0.6140   0.00709   0.00219  -0.0594   0.5566   1.0000
   3.250   0.6364   0.00722   0.00227  -0.0582   0.5362   1.0000
   3.500   0.6587   0.00736   0.00236  -0.0571   0.5151   1.0000
   3.750   0.6807   0.00753   0.00246  -0.0558   0.4899   1.0000
   4.000   0.7021   0.00775   0.00259  -0.0545   0.4607   1.0000
   4.250   0.7229   0.00802   0.00274  -0.0531   0.4268   1.0000
   4.500   0.7425   0.00839   0.00293  -0.0515   0.3803   1.0000
   4.750   0.7602   0.00891   0.00318  -0.0496   0.3160   1.0000
   5.000   0.7748   0.00972   0.00358  -0.0473   0.2297   1.0000
   5.250   0.7884   0.01066   0.00407  -0.0449   0.1452   1.0000
   5.500   0.8039   0.01146   0.00456  -0.0428   0.0876   1.0000
   5.750   0.8187   0.01235   0.00515  -0.0404   0.0425   1.0000
   6.000   0.8387   0.01281   0.00566  -0.0389   0.0371   1.0000
   6.250   0.8555   0.01353   0.00642  -0.0368   0.0319   1.0000
   6.500   0.8753   0.01399   0.00693  -0.0353   0.0297   1.0000
   6.750   0.8942   0.01451   0.00751  -0.0336   0.0275   1.0000
   7.000   0.9111   0.01519   0.00821  -0.0316   0.0256   1.0000
   7.250   0.9207   0.01646   0.00956  -0.0285   0.0236   1.0000
   7.500   0.9414   0.01683   0.00999  -0.0272   0.0224   1.0000
   7.750   0.9595   0.01741   0.01063  -0.0255   0.0212   1.0000
   8.000   0.9763   0.01812   0.01137  -0.0236   0.0202   1.0000
   8.250   0.9924   0.01888   0.01216  -0.0217   0.0192   1.0000
   8.500   1.0058   0.01999   0.01330  -0.0195   0.0185   1.0000
   8.750   1.0179   0.02178   0.01518  -0.0171   0.0176   1.0000
   9.000   1.0361   0.02240   0.01590  -0.0156   0.0170   1.0000
   9.250   1.0534   0.02310   0.01668  -0.0140   0.0161   1.0000
   9.500   1.0697   0.02413   0.01780  -0.0123   0.0155   1.0000
   9.750   1.0856   0.02516   0.01892  -0.0107   0.0150   1.0000
  10.000   1.1000   0.02613   0.01995  -0.0089   0.0144   1.0000
  10.250   1.1137   0.02746   0.02138  -0.0070   0.0141   1.0000
  10.500   1.1276   0.02938   0.02338  -0.0056   0.0136   1.0000
  10.750   1.1392   0.03324   0.02752  -0.0043   0.0132   1.0000
  11.000   1.1424   0.03436   0.02885  -0.0008   0.0130   1.0000
  11.250   1.1446   0.03658   0.03128   0.0022   0.0130   1.0000
  11.500   1.1428   0.03822   0.03316   0.0056   0.0128   1.0000
  11.750   1.1398   0.04027   0.03543   0.0086   0.0126   1.0000
  12.000   1.1331   0.04302   0.03840   0.0113   0.0126   1.0000
  12.250   1.1251   0.04531   0.04092   0.0136   0.0121   1.0000
  12.500   1.1066   0.04961   0.04549   0.0154   0.0124   1.0000
  12.750   1.0947   0.05284   0.04891   0.0163   0.0122   1.0000
  13.000   1.0794   0.05679   0.05307   0.0164   0.0120   1.0000
  13.250   1.0604   0.06172   0.05820   0.0157   0.0123   1.0000
  13.500   1.0419   0.06692   0.06358   0.0140   0.0122   1.0000
  13.750   1.0186   0.07336   0.07021   0.0111   0.0123   1.0000
  14.000   1.0006   0.07950   0.07649   0.0079   0.0124   1.0000
  14.250   0.9742   0.08781   0.08497   0.0029   0.0124   1.0000
  14.500   0.9534   0.09585   0.09312  -0.0020   0.0127   1.0000
  14.750   0.9250   0.10633   0.10372  -0.0085   0.0129   1.0000
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