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RAF-48 AIRFOIL (raf48-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: RAF-48 AIRFOIL (raf48-il)
Reynolds number: 200,000
Max Cl/Cd: 68.54 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf48-il-200000.txt
Download as CSV file: xf-raf48-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF-48 AIRFOIL                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.6386   0.06675   0.06262  -0.0731   1.0000   0.0516
 -12.500  -0.6693   0.05990   0.05566  -0.0772   1.0000   0.0512
 -12.250  -0.7046   0.05436   0.04995  -0.0791   1.0000   0.0510
 -12.000  -0.7354   0.05039   0.04580  -0.0780   1.0000   0.0508
 -11.750  -0.7624   0.04750   0.04274  -0.0744   1.0000   0.0508
 -11.500  -0.7906   0.04529   0.04036  -0.0687   1.0000   0.0509
 -11.250  -0.8122   0.04305   0.03789  -0.0635   1.0000   0.0511
 -11.000  -0.8325   0.04135   0.03599  -0.0576   1.0000   0.0514
 -10.750  -0.8584   0.04052   0.03505  -0.0502   1.0000   0.0515
 -10.500  -0.8462   0.03724   0.03146  -0.0508   0.9940   0.0527
 -10.250  -0.8124   0.03575   0.03000  -0.0534   0.9876   0.0545
 -10.000  -0.7808   0.03370   0.02772  -0.0559   0.9816   0.0562
  -9.750  -0.7546   0.03152   0.02516  -0.0572   0.9725   0.0581
  -9.500  -0.7264   0.02954   0.02271  -0.0586   0.9650   0.0599
  -9.250  -0.6919   0.02766   0.02086  -0.0609   0.9592   0.0621
  -9.000  -0.6537   0.02631   0.01938  -0.0636   0.9553   0.0644
  -8.750  -0.6224   0.02514   0.01798  -0.0648   0.9472   0.0670
  -8.500  -0.5865   0.02354   0.01619  -0.0669   0.9416   0.0697
  -8.250  -0.5517   0.02249   0.01515  -0.0687   0.9347   0.0724
  -8.000  -0.5191   0.02168   0.01422  -0.0698   0.9267   0.0760
  -7.750  -0.4868   0.02064   0.01303  -0.0709   0.9195   0.0793
  -7.500  -0.4588   0.01985   0.01227  -0.0711   0.9102   0.0828
  -7.250  -0.4316   0.01932   0.01165  -0.0710   0.9017   0.0874
  -7.000  -0.4069   0.01858   0.01089  -0.0705   0.8926   0.0922
  -6.750  -0.3834   0.01817   0.01046  -0.0697   0.8841   0.0978
  -6.500  -0.3603   0.01759   0.00984  -0.0687   0.8754   0.1046
  -6.250  -0.3381   0.01729   0.00949  -0.0675   0.8665   0.1130
  -6.000  -0.3161   0.01678   0.00901  -0.0663   0.8572   0.1230
  -5.750  -0.2956   0.01636   0.00859  -0.0648   0.8475   0.1348
  -5.500  -0.2727   0.01598   0.00820  -0.0636   0.8395   0.1489
  -5.250  -0.2511   0.01569   0.00791  -0.0624   0.8315   0.1633
  -5.000  -0.2281   0.01541   0.00762  -0.0614   0.8244   0.1783
  -4.750  -0.2043   0.01515   0.00736  -0.0605   0.8182   0.1937
  -4.500  -0.1823   0.01492   0.00716  -0.0593   0.8103   0.2095
  -4.250  -0.1583   0.01462   0.00689  -0.0585   0.8043   0.2275
  -4.000  -0.1363   0.01438   0.00674  -0.0573   0.7973   0.2470
  -3.750  -0.1136   0.01411   0.00654  -0.0562   0.7905   0.2707
  -3.250  -0.0701   0.01350   0.00618  -0.0537   0.7771   0.3361
  -3.000  -0.0491   0.01311   0.00600  -0.0523   0.7709   0.3861
  -2.750  -0.0301   0.01276   0.00591  -0.0504   0.7646   0.4531
  -2.500  -0.0126   0.01239   0.00586  -0.0482   0.7573   0.5274
  -2.250   0.0075   0.01205   0.00581  -0.0462   0.7517   0.6095
  -2.000   0.0273   0.01189   0.00591  -0.0441   0.7442   0.6829
  -1.750   0.0518   0.01178   0.00594  -0.0427   0.7372   0.7415
  -1.500   0.0789   0.01177   0.00598  -0.0418   0.7312   0.7874
  -1.250   0.1046   0.01181   0.00607  -0.0408   0.7232   0.8231
  -1.000   0.1383   0.01184   0.00606  -0.0413   0.7170   0.8532
  -0.750   0.1719   0.01192   0.00614  -0.0420   0.7090   0.8790
  -0.500   0.2169   0.01202   0.00617  -0.0448   0.7013   0.8981
  -0.250   0.2623   0.01220   0.00628  -0.0478   0.6933   0.9134
   0.000   0.3073   0.01238   0.00638  -0.0508   0.6849   0.9267
   0.250   0.3624   0.01266   0.00656  -0.0557   0.6766   0.9347
   0.500   0.4072   0.01282   0.00664  -0.0587   0.6672   0.9454
   0.750   0.4468   0.01296   0.00672  -0.0608   0.6581   0.9561
   1.000   0.4945   0.01302   0.00668  -0.0647   0.6487   0.9629
   1.250   0.5373   0.01312   0.00674  -0.0677   0.6384   0.9726
   1.500   0.5873   0.01316   0.00666  -0.0721   0.6293   0.9830
   1.750   0.6371   0.01308   0.00658  -0.0768   0.6177   0.9919
   2.000   0.6821   0.01294   0.00636  -0.0805   0.6078   0.9987
   2.250   0.7065   0.01290   0.00627  -0.0802   0.5983   1.0000
   2.500   0.7250   0.01293   0.00628  -0.0787   0.5892   1.0000
   2.750   0.7442   0.01294   0.00622  -0.0772   0.5804   1.0000
   3.000   0.7622   0.01298   0.00626  -0.0756   0.5707   1.0000
   3.250   0.7821   0.01301   0.00620  -0.0742   0.5624   1.0000
   3.500   0.7996   0.01308   0.00629  -0.0724   0.5524   1.0000
   3.750   0.8197   0.01315   0.00627  -0.0710   0.5445   1.0000
   4.000   0.8372   0.01324   0.00640  -0.0692   0.5350   1.0000
   4.250   0.8574   0.01337   0.00645  -0.0678   0.5274   1.0000
   4.500   0.8753   0.01350   0.00661  -0.0660   0.5184   1.0000
   4.750   0.8959   0.01366   0.00670  -0.0646   0.5108   1.0000
   5.000   0.9144   0.01383   0.00691  -0.0629   0.5019   1.0000
   5.250   0.9354   0.01402   0.00703  -0.0617   0.4944   1.0000
   5.500   0.9542   0.01421   0.00726  -0.0600   0.4855   1.0000
   5.750   0.9758   0.01444   0.00743  -0.0588   0.4781   1.0000
   6.000   0.9946   0.01465   0.00771  -0.0572   0.4694   1.0000
   6.250   1.0165   0.01491   0.00790  -0.0560   0.4618   1.0000
   6.500   1.0347   0.01514   0.00821  -0.0543   0.4528   1.0000
   6.750   1.0560   0.01542   0.00843  -0.0531   0.4446   1.0000
   7.000   1.0740   0.01567   0.00875  -0.0513   0.4353   1.0000
   7.250   1.0945   0.01597   0.00903  -0.0499   0.4270   1.0000
   7.500   1.1122   0.01623   0.00935  -0.0481   0.4174   1.0000
   7.750   1.1303   0.01653   0.00967  -0.0464   0.4076   1.0000
   8.000   1.1480   0.01680   0.00989  -0.0445   0.3965   1.0000
   8.250   1.1610   0.01704   0.01023  -0.0419   0.3839   1.0000
   8.500   1.1743   0.01732   0.01054  -0.0393   0.3708   1.0000
   8.750   1.1865   0.01761   0.01084  -0.0365   0.3572   1.0000
   9.000   1.1969   0.01794   0.01116  -0.0335   0.3429   1.0000
   9.250   1.2055   0.01832   0.01154  -0.0302   0.3281   1.0000
   9.500   1.2108   0.01876   0.01196  -0.0264   0.3127   1.0000
   9.750   1.2128   0.01925   0.01242  -0.0221   0.2984   1.0000
  10.000   1.2153   0.01986   0.01298  -0.0182   0.2841   1.0000
  10.250   1.2193   0.02057   0.01367  -0.0148   0.2701   1.0000
  10.500   1.2238   0.02139   0.01448  -0.0117   0.2567   1.0000
  10.750   1.2288   0.02230   0.01538  -0.0090   0.2445   1.0000
  11.000   1.2334   0.02333   0.01639  -0.0065   0.2330   1.0000
  11.250   1.2372   0.02450   0.01750  -0.0041   0.2227   1.0000
  11.500   1.2430   0.02563   0.01867  -0.0022   0.2114   1.0000
  11.750   1.2481   0.02689   0.01995  -0.0003   0.2011   1.0000
  12.000   1.2507   0.02837   0.02139   0.0016   0.1915   1.0000
  12.250   1.2557   0.02978   0.02286   0.0030   0.1810   1.0000
  12.500   1.2589   0.03138   0.02450   0.0044   0.1703   1.0000
  12.750   1.2595   0.03325   0.02638   0.0058   0.1593   1.0000
  13.000   1.2580   0.03539   0.02850   0.0070   0.1476   1.0000
  13.250   1.2546   0.03779   0.03089   0.0081   0.1345   1.0000
  13.500   1.2495   0.04048   0.03359   0.0090   0.1196   1.0000
  13.750   1.2422   0.04348   0.03656   0.0098   0.1060   1.0000
  14.000   1.2337   0.04675   0.03978   0.0104   0.0956   1.0000
  14.250   1.2269   0.04998   0.04299   0.0108   0.0870   1.0000
  14.500   1.2225   0.05307   0.04610   0.0110   0.0804   1.0000
  14.750   1.2159   0.05647   0.04947   0.0111   0.0759   1.0000
  15.000   1.2137   0.05947   0.05253   0.0112   0.0717   1.0000
  15.250   1.2111   0.06258   0.05567   0.0111   0.0684   1.0000
  15.500   1.2065   0.06586   0.05890   0.0111   0.0655   1.0000
  15.750   1.2073   0.06869   0.06184   0.0109   0.0627   1.0000
  16.000   1.2074   0.07157   0.06477   0.0108   0.0604   1.0000
  16.250   1.2067   0.07443   0.06758   0.0107   0.0580   1.0000
  16.500   1.2096   0.07688   0.07008   0.0109   0.0561   1.0000
  16.750   1.2111   0.07972   0.07302   0.0106   0.0541   1.0000
  17.000   1.2140   0.08227   0.07562   0.0104   0.0523   1.0000
  17.250   1.2191   0.08432   0.07760   0.0107   0.0503   1.0000
  17.500   1.2257   0.08624   0.07956   0.0111   0.0488   1.0000
  17.750   1.2239   0.08972   0.08321   0.0102   0.0472   1.0000
  18.000   1.2270   0.09235   0.08592   0.0099   0.0460   1.0000
  18.250   1.2318   0.09467   0.08826   0.0098   0.0446   1.0000
  18.500   1.2453   0.09540   0.08890   0.0108   0.0430   1.0000
  18.750   1.2454   0.09854   0.09217   0.0103   0.0421   1.0000
  19.000   1.2393   0.10282   0.09665   0.0087   0.0413   1.0000
  19.250   1.2352   0.10677   0.10076   0.0074   0.0403   1.0000
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