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RAF 30 AIRFOIL (raf30-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: RAF 30 AIRFOIL (raf30-il)
Reynolds number: 100,000
Max Cl/Cd: 41.72 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf30-il-100000.txt
Download as CSV file: xf-raf30-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 30 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.7953   0.08460   0.07896  -0.0399   1.0000   0.0787
 -12.250  -0.7997   0.07897   0.07332  -0.0410   1.0000   0.0778
 -12.000  -0.8258   0.07294   0.06719  -0.0432   1.0000   0.0772
 -11.750  -0.8497   0.06793   0.06206  -0.0439   1.0000   0.0765
 -11.500  -0.8739   0.06364   0.05761  -0.0433   1.0000   0.0758
 -11.250  -0.8993   0.06009   0.05387  -0.0408   1.0000   0.0757
 -11.000  -0.9199   0.05691   0.05049  -0.0372   1.0000   0.0754
 -10.750  -0.9348   0.05365   0.04696  -0.0339   1.0000   0.0755
 -10.500  -0.9443   0.05048   0.04347  -0.0307   1.0000   0.0758
 -10.250  -0.9487   0.04744   0.04007  -0.0276   1.0000   0.0761
 -10.000  -0.9487   0.04450   0.03676  -0.0246   1.0000   0.0766
  -9.750  -0.9445   0.04175   0.03362  -0.0219   1.0000   0.0771
  -9.500  -0.9379   0.03949   0.03094  -0.0191   1.0000   0.0781
  -9.250  -0.9251   0.03681   0.02802  -0.0173   1.0000   0.0800
  -9.000  -0.9072   0.03488   0.02605  -0.0162   1.0000   0.0825
  -8.750  -0.8893   0.03310   0.02411  -0.0147   1.0000   0.0848
  -8.500  -0.8705   0.03141   0.02222  -0.0132   1.0000   0.0873
  -8.250  -0.8529   0.03009   0.02059  -0.0114   1.0000   0.0906
  -8.000  -0.8296   0.02818   0.01877  -0.0108   1.0000   0.0945
  -7.750  -0.8084   0.02686   0.01745  -0.0097   1.0000   0.0987
  -7.500  -0.7881   0.02572   0.01613  -0.0082   1.0000   0.1039
  -7.250  -0.7689   0.02432   0.01493  -0.0069   1.0000   0.1111
  -7.000  -0.7515   0.02314   0.01376  -0.0050   1.0000   0.1204
  -6.750  -0.7371   0.02192   0.01267  -0.0027   1.0000   0.1340
  -6.500  -0.7279   0.02054   0.01157   0.0004   1.0000   0.1594
  -6.250  -0.7224   0.01912   0.01059   0.0040   1.0000   0.2068
  -6.000  -0.7153   0.01810   0.00996   0.0074   1.0000   0.2621
  -5.750  -0.7054   0.01739   0.00948   0.0105   1.0000   0.3140
  -5.500  -0.6945   0.01682   0.00913   0.0135   1.0000   0.3598
  -5.250  -0.6829   0.01638   0.00889   0.0164   1.0000   0.4025
  -5.000  -0.6709   0.01608   0.00875   0.0193   1.0000   0.4448
  -4.750  -0.6590   0.01590   0.00871   0.0223   1.0000   0.4868
  -4.500  -0.6464   0.01583   0.00878   0.0253   1.0000   0.5252
  -4.250  -0.6332   0.01583   0.00888   0.0282   1.0000   0.5604
  -4.000  -0.6191   0.01585   0.00896   0.0309   1.0000   0.5913
  -3.750  -0.6046   0.01587   0.00900   0.0334   1.0000   0.6194
  -3.500  -0.5892   0.01590   0.00907   0.0358   1.0000   0.6443
  -3.250  -0.5742   0.01594   0.00914   0.0382   1.0000   0.6685
  -3.000  -0.5589   0.01601   0.00924   0.0405   1.0000   0.6915
  -2.750  -0.5446   0.01608   0.00932   0.0428   1.0000   0.7152
  -2.500  -0.5229   0.01629   0.00959   0.0440   0.9977   0.7399
  -2.250  -0.4821   0.01676   0.01009   0.0419   0.9881   0.7695
  -2.000  -0.4422   0.01712   0.01044   0.0398   0.9785   0.7965
  -1.750  -0.3962   0.01745   0.01076   0.0365   0.9702   0.8168
  -1.500  -0.3559   0.01763   0.01092   0.0343   0.9599   0.8358
  -1.250  -0.3108   0.01787   0.01112   0.0312   0.9508   0.8536
  -1.000  -0.2578   0.01814   0.01135   0.0266   0.9429   0.8694
  -0.750  -0.2067   0.01839   0.01157   0.0224   0.9335   0.8836
  -0.500  -0.1423   0.01860   0.01174   0.0157   0.9268   0.8955
  -0.250  -0.0773   0.01879   0.01192   0.0090   0.9178   0.9046
   0.000   0.0002   0.01881   0.01192   0.0000   0.9119   0.9120
   0.250   0.0772   0.01879   0.01191  -0.0089   0.9045   0.9178
   0.500   0.1424   0.01859   0.01173  -0.0157   0.8955   0.9268
   0.750   0.2069   0.01839   0.01157  -0.0224   0.8836   0.9336
   1.000   0.2579   0.01814   0.01135  -0.0266   0.8694   0.9429
   1.250   0.3108   0.01787   0.01113  -0.0312   0.8537   0.9509
   1.500   0.3558   0.01763   0.01091  -0.0343   0.8357   0.9599
   1.750   0.3960   0.01745   0.01076  -0.0365   0.8168   0.9701
   2.000   0.4423   0.01711   0.01043  -0.0398   0.7965   0.9786
   2.250   0.4821   0.01675   0.01008  -0.0419   0.7694   0.9881
   2.500   0.5230   0.01629   0.00959  -0.0440   0.7398   0.9978
   2.750   0.5445   0.01608   0.00932  -0.0428   0.7153   1.0000
   3.000   0.5588   0.01601   0.00925  -0.0405   0.6916   1.0000
   3.250   0.5741   0.01594   0.00914  -0.0381   0.6685   1.0000
   3.500   0.5892   0.01590   0.00907  -0.0358   0.6444   1.0000
   3.750   0.6045   0.01587   0.00900  -0.0334   0.6194   1.0000
   4.000   0.6189   0.01585   0.00896  -0.0308   0.5911   1.0000
   4.250   0.6330   0.01583   0.00887  -0.0281   0.5600   1.0000
   4.500   0.6463   0.01583   0.00877  -0.0253   0.5251   1.0000
   4.750   0.6588   0.01590   0.00870  -0.0223   0.4865   1.0000
   5.000   0.6708   0.01608   0.00875  -0.0193   0.4449   1.0000
   5.250   0.6828   0.01638   0.00889  -0.0164   0.4024   1.0000
   5.500   0.6945   0.01681   0.00912  -0.0134   0.3597   1.0000
   5.750   0.7053   0.01739   0.00948  -0.0105   0.3138   1.0000
   6.000   0.7153   0.01810   0.00996  -0.0074   0.2618   1.0000
   6.250   0.7223   0.01913   0.01059  -0.0040   0.2066   1.0000
   6.500   0.7279   0.02054   0.01157  -0.0004   0.1590   1.0000
   6.750   0.7372   0.02191   0.01267   0.0027   0.1340   1.0000
   7.000   0.7514   0.02314   0.01377   0.0050   0.1203   1.0000
   7.250   0.7689   0.02432   0.01493   0.0069   0.1110   1.0000
   7.500   0.7881   0.02572   0.01614   0.0082   0.1038   1.0000
   7.750   0.8085   0.02686   0.01745   0.0097   0.0988   1.0000
   8.000   0.8297   0.02818   0.01878   0.0108   0.0945   1.0000
   8.250   0.8529   0.03008   0.02059   0.0114   0.0906   1.0000
   8.500   0.8705   0.03141   0.02223   0.0132   0.0873   1.0000
   8.750   0.8893   0.03310   0.02412   0.0147   0.0847   1.0000
   9.000   0.9073   0.03489   0.02607   0.0162   0.0825   1.0000
   9.250   0.9252   0.03681   0.02802   0.0173   0.0800   1.0000
   9.500   0.9380   0.03952   0.03095   0.0190   0.0782   1.0000
   9.750   0.9446   0.04176   0.03363   0.0219   0.0771   1.0000
  10.000   0.9490   0.04451   0.03676   0.0246   0.0766   1.0000
  10.250   0.9491   0.04743   0.04006   0.0276   0.0762   1.0000
  10.500   0.9440   0.05041   0.04340   0.0308   0.0755   1.0000
  10.750   0.9345   0.05358   0.04689   0.0340   0.0753   1.0000
  11.000   0.9197   0.05684   0.05042   0.0372   0.0752   1.0000
  11.250   0.8982   0.06000   0.05379   0.0409   0.0753   1.0000
  11.500   0.8744   0.06362   0.05759   0.0432   0.0758   1.0000
  11.750   0.8502   0.06794   0.06207   0.0438   0.0765   1.0000
  12.000   0.8269   0.07294   0.06719   0.0431   0.0772   1.0000
  12.250   0.8051   0.07868   0.07301   0.0412   0.0779   1.0000
  12.500   0.7957   0.08464   0.07900   0.0397   0.0787   1.0000
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