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RAF 6 AIRFOIL (raf6-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RAF 6 AIRFOIL (raf6-il)
Reynolds number: 200,000
Max Cl/Cd: 68.19 at α=1.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf6-il-200000-n5.txt
Download as CSV file: xf-raf6-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 6 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3291   0.11931   0.11585  -0.0280   1.0000   0.0173
  -9.500  -0.3311   0.11696   0.11355  -0.0279   1.0000   0.0176
  -9.250  -0.3355   0.11486   0.11150  -0.0279   1.0000   0.0178
  -9.000  -0.3296   0.11156   0.10823  -0.0323   0.9979   0.0180
  -8.750  -0.3183   0.10768   0.10436  -0.0377   0.9951   0.0181
  -8.500  -0.3077   0.10377   0.10046  -0.0425   0.9912   0.0182
  -8.250  -0.2975   0.09874   0.09546  -0.0439   0.9889   0.0185
  -8.000  -0.2832   0.09484   0.09155  -0.0448   0.9872   0.0189
  -7.750  -0.2727   0.09131   0.08803  -0.0472   0.9827   0.0192
  -7.500  -0.2603   0.08759   0.08432  -0.0510   0.9786   0.0196
  -7.250  -0.2474   0.08367   0.08042  -0.0552   0.9720   0.0200
  -7.000  -0.2285   0.07927   0.07600  -0.0611   0.9672   0.0205
  -6.750  -0.2121   0.07510   0.07181  -0.0663   0.9606   0.0211
  -6.500  -0.1943   0.07090   0.06758  -0.0714   0.9539   0.0217
  -6.000  -0.1460   0.06221   0.05869  -0.0830   0.9410   0.0237
  -5.750  -0.1110   0.05844   0.05470  -0.0888   0.9369   0.0245
  -5.500  -0.0911   0.05509   0.05120  -0.0903   0.9298   0.0247
  -5.250  -0.0655   0.05133   0.04725  -0.0928   0.9255   0.0248
  -4.250   0.0311   0.03306   0.02804  -0.0988   0.9094   0.0175
  -4.000   0.0515   0.03050   0.02524  -0.0980   0.9024   0.0171
  -3.750   0.0811   0.02754   0.02193  -0.0986   0.8985   0.0167
  -3.500   0.1156   0.02457   0.01853  -0.0997   0.8957   0.0167
  -3.250   0.1484   0.02221   0.01565  -0.0999   0.8911   0.0180
  -3.000   0.1766   0.02019   0.01326  -0.0996   0.8846   0.0184
  -2.750   0.2126   0.01847   0.01129  -0.1012   0.8807   0.0191
  -2.500   0.2475   0.01732   0.00995  -0.1023   0.8748   0.0203
  -2.250   0.2814   0.01644   0.00892  -0.1032   0.8659   0.0228
  -2.000   0.3184   0.01532   0.00760  -0.1045   0.8558   0.0243
  -1.750   0.3578   0.01405   0.00621  -0.1066   0.8447   0.0277
  -1.500   0.3914   0.01340   0.00549  -0.1075   0.8320   0.0313
  -1.250   0.4219   0.01298   0.00496  -0.1079   0.8210   0.0360
  -1.000   0.4533   0.01250   0.00441  -0.1085   0.8116   0.0414
  -0.750   0.4823   0.01228   0.00410  -0.1086   0.8007   0.0499
  -0.500   0.5099   0.01203   0.00382  -0.1084   0.7898   0.0647
  -0.250   0.5315   0.01045   0.00375  -0.1080   0.7790   0.5577
   0.000   0.5808   0.00962   0.00373  -0.1114   0.7647   1.0000
   0.250   0.6050   0.00969   0.00364  -0.1105   0.7480   1.0000
   0.500   0.6286   0.00977   0.00357  -0.1095   0.7281   1.0000
   0.750   0.6527   0.00986   0.00350  -0.1085   0.7038   1.0000
   1.000   0.6762   0.00999   0.00342  -0.1074   0.6709   1.0000
   1.250   0.6976   0.01023   0.00334  -0.1058   0.6232   1.0000
   1.500   0.7155   0.01063   0.00336  -0.1036   0.5634   1.0000
   1.750   0.7317   0.01114   0.00348  -0.1011   0.5067   1.0000
   2.000   0.7494   0.01162   0.00366  -0.0991   0.4638   1.0000
   2.250   0.7689   0.01204   0.00385  -0.0975   0.4329   1.0000
   2.500   0.7895   0.01242   0.00405  -0.0962   0.4075   1.0000
   2.750   0.8106   0.01279   0.00426  -0.0949   0.3838   1.0000
   3.000   0.8317   0.01316   0.00448  -0.0937   0.3616   1.0000
   3.250   0.8534   0.01350   0.00470  -0.0926   0.3409   1.0000
   3.500   0.8752   0.01385   0.00493  -0.0916   0.3227   1.0000
   3.750   0.8970   0.01419   0.00519  -0.0905   0.3074   1.0000
   4.000   0.9188   0.01454   0.00544  -0.0895   0.2942   1.0000
   4.250   0.9405   0.01490   0.00572  -0.0885   0.2822   1.0000
   4.500   0.9627   0.01524   0.00602  -0.0876   0.2719   1.0000
   4.750   0.9843   0.01561   0.00632  -0.0866   0.2637   1.0000
   5.000   1.0067   0.01594   0.00664  -0.0857   0.2566   1.0000
   5.250   1.0278   0.01634   0.00700  -0.0846   0.2503   1.0000
   5.500   1.0503   0.01666   0.00734  -0.0838   0.2440   1.0000
   5.750   1.0716   0.01705   0.00771  -0.0827   0.2382   1.0000
   6.000   1.0930   0.01743   0.00810  -0.0818   0.2332   1.0000
   6.250   1.1146   0.01777   0.00849  -0.0808   0.2281   1.0000
   6.500   1.1348   0.01818   0.00889  -0.0796   0.2233   1.0000
   6.750   1.1551   0.01860   0.00934  -0.0784   0.2191   1.0000
   7.000   1.1765   0.01895   0.00978  -0.0774   0.2146   1.0000
   7.250   1.1968   0.01937   0.01023  -0.0763   0.2101   1.0000
   7.500   1.2160   0.01987   0.01074  -0.0750   0.2062   1.0000
   7.750   1.2370   0.02027   0.01124  -0.0740   0.2025   1.0000
   8.000   1.2578   0.02068   0.01176  -0.0730   0.1985   1.0000
   8.250   1.2774   0.02114   0.01229  -0.0719   0.1944   1.0000
   8.500   1.2958   0.02168   0.01287  -0.0705   0.1906   1.0000
   8.750   1.3156   0.02216   0.01346  -0.0694   0.1868   1.0000
   9.000   1.3344   0.02255   0.01399  -0.0682   0.1804   1.0000
   9.250   1.3502   0.02302   0.01450  -0.0665   0.1720   1.0000
   9.500   1.3669   0.02345   0.01500  -0.0650   0.1616   1.0000
   9.750   1.3842   0.02393   0.01556  -0.0637   0.1511   1.0000
  10.000   1.4003   0.02452   0.01620  -0.0622   0.1398   1.0000
  10.250   1.4135   0.02531   0.01693  -0.0605   0.1212   1.0000
  10.500   1.4219   0.02655   0.01801  -0.0582   0.0927   1.0000
  10.750   1.4127   0.02930   0.02028  -0.0541   0.0317   1.0000
  11.000   1.4125   0.03133   0.02235  -0.0509   0.0201   1.0000
  11.250   1.4166   0.03302   0.02419  -0.0484   0.0169   1.0000
  11.500   1.4208   0.03473   0.02607  -0.0461   0.0149   1.0000
  11.750   1.4229   0.03664   0.02815  -0.0439   0.0135   1.0000
  12.000   1.4261   0.03850   0.03020  -0.0419   0.0124   1.0000
  12.250   1.4264   0.04068   0.03257  -0.0400   0.0117   1.0000
  12.500   1.4230   0.04328   0.03535  -0.0381   0.0112   1.0000
  12.750   1.4193   0.04603   0.03830  -0.0366   0.0107   1.0000
  13.000   1.4153   0.04893   0.04141  -0.0353   0.0103   1.0000
  13.250   1.4087   0.05225   0.04492  -0.0344   0.0099   1.0000
  13.500   1.3998   0.05605   0.04894  -0.0339   0.0095   1.0000
  13.750   1.3889   0.06042   0.05349  -0.0340   0.0092   1.0000
  14.000   1.3754   0.06549   0.05874  -0.0348   0.0090   1.0000
  14.250   1.3596   0.07132   0.06477  -0.0363   0.0089   1.0000
  14.500   1.3423   0.07791   0.07154  -0.0386   0.0089   1.0000
  14.750   1.3237   0.08506   0.07889  -0.0415   0.0088   1.0000
  15.000   1.3043   0.09264   0.08665  -0.0446   0.0088   1.0000
  15.250   1.2848   0.10032   0.09450  -0.0478   0.0089   1.0000
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