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RAF-48 AIRFOIL (raf48-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: RAF-48 AIRFOIL (raf48-il)
Reynolds number: 50,000
Max Cl/Cd: 7.42 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf48-il-50000.txt
Download as CSV file: xf-raf48-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3344   0.11561   0.10831  -0.0274   1.0000   0.3119
 -10.000  -0.3001   0.10988   0.10254  -0.0267   1.0000   0.3211
  -9.750  -0.3254   0.10925   0.10207  -0.0266   1.0000   0.3305
  -9.500  -0.2949   0.10445   0.09722  -0.0259   1.0000   0.3403
  -9.250  -0.3028   0.10224   0.09512  -0.0253   1.0000   0.3505
  -9.000  -0.3159   0.10121   0.09421  -0.0239   1.0000   0.3644
  -8.750  -0.2891   0.09670   0.08970  -0.0232   1.0000   0.3743
  -8.500  -0.3060   0.09516   0.08832  -0.0216   1.0000   0.3847
  -8.250  -0.2946   0.09225   0.08545  -0.0202   1.0000   0.3942
  -8.000  -0.5945   0.07611   0.06985  -0.0296   1.0000   0.1926
  -7.750  -0.5990   0.07324   0.06698  -0.0271   1.0000   0.1901
  -7.500  -0.6121   0.07010   0.06382  -0.0245   1.0000   0.1873
  -7.250  -0.6745   0.06262   0.05569  -0.0219   1.0000   0.1755
  -7.000  -0.6783   0.05927   0.05218  -0.0197   1.0000   0.1749
  -6.750  -0.6821   0.05586   0.04850  -0.0174   1.0000   0.1745
  -6.500  -0.6863   0.05247   0.04468  -0.0149   1.0000   0.1751
  -6.250  -0.6781   0.05022   0.04240  -0.0131   1.0000   0.1785
  -6.000  -0.6701   0.04820   0.04023  -0.0112   1.0000   0.1820
  -5.750  -0.6633   0.04573   0.03742  -0.0092   1.0000   0.1848
  -5.500  -0.6557   0.04336   0.03457  -0.0072   1.0000   0.1891
  -5.250  -0.6452   0.04134   0.03223  -0.0053   1.0000   0.1947
  -5.000  -0.6311   0.04005   0.03087  -0.0038   1.0000   0.2015
  -4.750  -0.6189   0.03832   0.02864  -0.0019   1.0000   0.2097
  -4.500  -0.6036   0.03728   0.02766  -0.0005   1.0000   0.2193
  -4.250  -0.5888   0.03604   0.02622   0.0010   1.0000   0.2303
  -4.000  -0.5736   0.03505   0.02502   0.0025   1.0000   0.2443
  -3.750  -0.5415   0.03439   0.02439   0.0009   0.9937   0.2656
  -3.500  -0.5031   0.03389   0.02372  -0.0017   0.9834   0.2951
  -3.250  -0.4674   0.03341   0.02337  -0.0039   0.9729   0.3267
  -3.000  -0.4323   0.03306   0.02309  -0.0058   0.9624   0.3640
  -2.750  -0.3941   0.03283   0.02314  -0.0081   0.9521   0.4087
  -2.500  -0.3581   0.03254   0.02311  -0.0099   0.9412   0.4653
  -2.250  -0.3282   0.03211   0.02313  -0.0104   0.9306   0.5404
  -2.000  -0.2930   0.03177   0.02385  -0.0100   0.9213   0.6902
  -1.750   0.0543   0.03555   0.02724  -0.0615   0.9110   1.0000
  -1.500   0.0619   0.03548   0.02698  -0.0611   0.8984   1.0000
  -1.250   0.0852   0.03567   0.02695  -0.0624   0.8869   1.0000
  -1.000   0.0956   0.03595   0.02706  -0.0613   0.8744   1.0000
  -0.750   0.0975   0.03638   0.02735  -0.0587   0.8620   1.0000
  -0.500   0.1173   0.03691   0.02771  -0.0586   0.8509   1.0000
  -0.250   0.1352   0.03747   0.02811  -0.0581   0.8399   1.0000
   0.000   0.1352   0.03818   0.02869  -0.0549   0.8286   1.0000
   0.250   0.1727   0.03886   0.02920  -0.0571   0.8194   1.0000
   0.500   0.1645   0.03971   0.02993  -0.0526   0.8083   1.0000
   0.750   0.1847   0.04057   0.03067  -0.0523   0.7993   1.0000
   1.000   0.1920   0.04150   0.03148  -0.0501   0.7900   1.0000
   1.250   0.2080   0.04247   0.03234  -0.0492   0.7812   1.0000
   1.500   0.2177   0.04349   0.03326  -0.0474   0.7725   1.0000
   1.750   0.2362   0.04456   0.03424  -0.0468   0.7648   1.0000
   2.000   0.2386   0.04573   0.03532  -0.0443   0.7567   1.0000
   2.250   0.2695   0.04677   0.03629  -0.0452   0.7490   1.0000
   2.500   0.2610   0.04814   0.03759  -0.0415   0.7418   1.0000
   2.750   0.2936   0.04921   0.03860  -0.0427   0.7340   1.0000
   3.000   0.2881   0.05069   0.04002  -0.0395   0.7272   1.0000
   3.250   0.3017   0.05199   0.04127  -0.0386   0.7199   1.0000
   3.500   0.3201   0.05333   0.04257  -0.0382   0.7122   1.0000
   3.750   0.3209   0.05487   0.04408  -0.0361   0.7058   1.0000
   4.000   0.3555   0.05607   0.04526  -0.0373   0.6966   1.0000
   4.250   0.3469   0.05777   0.04693  -0.0345   0.6902   1.0000
   4.500   0.3852   0.05892   0.04807  -0.0358   0.6796   1.0000
   4.750   0.3740   0.06076   0.04989  -0.0330   0.6730   1.0000
   5.000   0.4085   0.06196   0.05110  -0.0338   0.6617   1.0000
   5.250   0.4010   0.06385   0.05299  -0.0316   0.6543   1.0000
   5.500   0.4269   0.06519   0.05433  -0.0317   0.6428   1.0000
   5.750   0.4377   0.06678   0.05595  -0.0308   0.6327   1.0000
   6.000   0.4459   0.06856   0.05774  -0.0298   0.6223   1.0000
   6.250   0.4726   0.06980   0.05900  -0.0297   0.6091   1.0000
   6.500   0.5096   0.07064   0.05990  -0.0301   0.5950   1.0000
   6.750   0.4895   0.07338   0.06264  -0.0279   0.5862   1.0000
   7.000   0.5080   0.07488   0.06418  -0.0273   0.5730   1.0000
   7.250   0.5346   0.07610   0.06546  -0.0271   0.5595   1.0000
   7.500   0.5699   0.07680   0.06624  -0.0270   0.5452   1.0000
   7.750   0.5455   0.08032   0.06974  -0.0254   0.5358   1.0000
   8.000   0.5606   0.08210   0.07158  -0.0248   0.5231   1.0000
   8.250   0.5834   0.08342   0.07297  -0.0243   0.5093   1.0000
   8.500   0.5986   0.08528   0.07488  -0.0239   0.4979   1.0000
   8.750   0.5895   0.08861   0.07824  -0.0232   0.4880   1.0000
   9.000   0.6090   0.09032   0.08003  -0.0228   0.4757   1.0000
   9.250   0.6076   0.09355   0.08330  -0.0226   0.4677   1.0000
   9.500   0.6143   0.09618   0.08598  -0.0223   0.4572   1.0000
   9.750   0.5639   0.10604   0.09588  -0.0261   0.4997   1.0000
  10.000   0.5813   0.10797   0.09787  -0.0256   0.4824   1.0000
  10.250   0.5990   0.11168   0.10165  -0.0264   0.4787   1.0000
  10.500   0.6465   0.10827   0.09833  -0.0226   0.4283   1.0000
  10.750   0.6518   0.11276   0.10290  -0.0236   0.4296   1.0000
  11.000   0.5607   0.12419   0.11428  -0.0294   0.5074   1.0000
  11.250   0.5968   0.12872   0.11893  -0.0305   0.4958   1.0000
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