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RAF 6 AIRFOIL (raf6-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: RAF 6 AIRFOIL (raf6-il)
Reynolds number: 1,000,000
Max Cl/Cd: 104.8 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf6-il-1000000.txt
Download as CSV file: xf-raf6-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3935   0.11517   0.11354  -0.0234   1.0000   0.0104
 -10.000  -0.3946   0.11196   0.11034  -0.0238   1.0000   0.0104
  -9.750  -0.3956   0.10887   0.10727  -0.0240   1.0000   0.0105
  -9.500  -0.3971   0.10579   0.10421  -0.0240   1.0000   0.0105
  -9.250  -0.3914   0.10181   0.10024  -0.0264   0.9994   0.0105
  -9.000  -0.3867   0.09644   0.09488  -0.0300   0.9982   0.0106
  -8.750  -0.3753   0.09293   0.09137  -0.0324   0.9971   0.0107
  -8.500  -0.3632   0.08931   0.08775  -0.0358   0.9959   0.0108
  -8.250  -0.3505   0.08548   0.08393  -0.0401   0.9947   0.0110
  -8.000  -0.3429   0.08174   0.08020  -0.0438   0.9915   0.0111
  -7.750  -0.3271   0.07691   0.07537  -0.0511   0.9881   0.0113
  -7.500  -0.3047   0.07147   0.06989  -0.0599   0.9862   0.0117
  -7.250  -0.2797   0.06566   0.06403  -0.0689   0.9848   0.0124
  -7.000  -0.2578   0.05711   0.05532  -0.0779   0.9778   0.0134
  -6.750  -0.2315   0.05132   0.04939  -0.0833   0.9758   0.0135
  -6.500  -0.2100   0.04448   0.04238  -0.0886   0.9742   0.0138
  -6.250  -0.1805   0.04151   0.03932  -0.0921   0.9734   0.0140
  -6.000  -0.1644   0.03913   0.03685  -0.0916   0.9665   0.0142
  -5.750  -0.1342   0.03620   0.03379  -0.0942   0.9645   0.0147
  -5.500  -0.1007   0.03259   0.02997  -0.0969   0.9630   0.0161
  -5.000  -0.0521   0.02231   0.01885  -0.0964   0.9536   0.0176
  -4.750  -0.0220   0.02114   0.01760  -0.0976   0.9496   0.0180
  -4.500  -0.0046   0.01307   0.00853  -0.0944   0.9426   0.0149
  -4.250   0.0243   0.01216   0.00748  -0.0945   0.9354   0.0157
  -4.000   0.0521   0.01124   0.00639  -0.0942   0.9250   0.0166
  -3.750   0.0832   0.01051   0.00550  -0.0947   0.9111   0.0171
  -3.500   0.1139   0.00944   0.00430  -0.0952   0.8912   0.0181
  -3.250   0.1431   0.00917   0.00392  -0.0954   0.8687   0.0189
  -3.000   0.1703   0.00893   0.00356  -0.0951   0.8504   0.0199
  -2.750   0.1971   0.00877   0.00329  -0.0947   0.8360   0.0209
  -2.500   0.2228   0.00836   0.00280  -0.0941   0.8243   0.0223
  -2.250   0.2493   0.00820   0.00260  -0.0937   0.8135   0.0236
  -2.000   0.2759   0.00808   0.00242  -0.0934   0.8037   0.0251
  -1.750   0.3030   0.00796   0.00227  -0.0931   0.7944   0.0264
  -1.500   0.3291   0.00771   0.00197  -0.0926   0.7849   0.0290
  -1.250   0.3558   0.00764   0.00187  -0.0923   0.7735   0.0313
  -1.000   0.3824   0.00758   0.00177  -0.0919   0.7601   0.0333
  -0.750   0.4085   0.00744   0.00158  -0.0914   0.7450   0.0378
  -0.500   0.4344   0.00743   0.00151  -0.0908   0.7266   0.0418
  -0.250   0.4595   0.00740   0.00140  -0.0901   0.6991   0.0500
   0.000   0.4823   0.00750   0.00135  -0.0889   0.6530   0.0669
   0.250   0.4932   0.00603   0.00146  -0.0863   0.5910   0.7332
   0.500   0.5031   0.00600   0.00172  -0.0819   0.5175   0.9415
   0.750   0.5425   0.00652   0.00192  -0.0844   0.4488   0.9883
   1.000   0.5910   0.00690   0.00206  -0.0892   0.4077   0.9968
   1.250   0.6301   0.00717   0.00214  -0.0918   0.3774   1.0000
   1.500   0.6513   0.00735   0.00220  -0.0904   0.3523   1.0000
   1.750   0.6724   0.00756   0.00226  -0.0891   0.3266   1.0000
   2.250   0.7151   0.00798   0.00242  -0.0864   0.2822   1.0000
   2.500   0.7372   0.00817   0.00252  -0.0852   0.2658   1.0000
   2.750   0.7596   0.00836   0.00262  -0.0841   0.2531   1.0000
   3.000   0.7824   0.00855   0.00273  -0.0831   0.2428   1.0000
   3.250   0.8063   0.00869   0.00284  -0.0823   0.2361   1.0000
   3.500   0.8299   0.00888   0.00297  -0.0814   0.2286   1.0000
   3.750   0.8546   0.00902   0.00309  -0.0808   0.2235   1.0000
   4.000   0.8792   0.00918   0.00321  -0.0802   0.2185   1.0000
   4.250   0.9033   0.00939   0.00338  -0.0795   0.2127   1.0000
   4.500   0.9288   0.00951   0.00350  -0.0790   0.2093   1.0000
   4.750   0.9539   0.00966   0.00364  -0.0785   0.2054   1.0000
   5.000   0.9786   0.00985   0.00381  -0.0780   0.2013   1.0000
   5.250   1.0031   0.01007   0.00401  -0.0774   0.1970   1.0000
   5.500   1.0287   0.01019   0.00415  -0.0770   0.1942   1.0000
   5.750   1.0538   0.01035   0.00431  -0.0766   0.1905   1.0000
   6.000   1.0784   0.01056   0.00450  -0.0761   0.1868   1.0000
   6.250   1.1024   0.01080   0.00473  -0.0754   0.1827   1.0000
   6.500   1.1279   0.01094   0.00490  -0.0751   0.1805   1.0000
   6.750   1.1528   0.01111   0.00509  -0.0746   0.1772   1.0000
   7.000   1.1771   0.01132   0.00529  -0.0741   0.1729   1.0000
   7.250   1.2013   0.01154   0.00550  -0.0735   0.1675   1.0000
   7.500   1.2261   0.01170   0.00568  -0.0731   0.1625   1.0000
   7.750   1.2496   0.01196   0.00591  -0.0724   0.1572   1.0000
   8.000   1.2737   0.01217   0.00615  -0.0719   0.1530   1.0000
   8.250   1.2975   0.01239   0.00637  -0.0713   0.1478   1.0000
   8.500   1.3201   0.01269   0.00664  -0.0705   0.1413   1.0000
   8.750   1.3435   0.01291   0.00690  -0.0699   0.1361   1.0000
   9.000   1.3653   0.01326   0.00721  -0.0690   0.1290   1.0000
   9.250   1.3877   0.01353   0.00750  -0.0682   0.1227   1.0000
   9.500   1.4083   0.01391   0.00785  -0.0671   0.1143   1.0000
   9.750   1.4272   0.01436   0.00825  -0.0657   0.1042   1.0000
  10.000   1.4448   0.01489   0.00872  -0.0641   0.0913   1.0000
  10.250   1.4570   0.01581   0.00946  -0.0617   0.0666   1.0000
  10.500   1.4557   0.01776   0.01109  -0.0571   0.0239   1.0000
  10.750   1.4696   0.01854   0.01190  -0.0550   0.0191   1.0000
  11.000   1.4840   0.01928   0.01268  -0.0530   0.0165   1.0000
  11.250   1.4992   0.01993   0.01339  -0.0512   0.0151   1.0000
  11.500   1.5119   0.02075   0.01426  -0.0490   0.0137   1.0000
  11.750   1.5243   0.02158   0.01517  -0.0469   0.0127   1.0000
  12.000   1.5382   0.02228   0.01595  -0.0451   0.0121   1.0000
  12.250   1.5508   0.02308   0.01681  -0.0431   0.0113   1.0000
  12.500   1.5610   0.02403   0.01782  -0.0409   0.0106   1.0000
  12.750   1.5642   0.02550   0.01941  -0.0379   0.0098   1.0000
  13.000   1.5758   0.02638   0.02036  -0.0362   0.0096   1.0000
  13.250   1.5851   0.02743   0.02149  -0.0342   0.0092   1.0000
  13.500   1.5930   0.02862   0.02277  -0.0322   0.0088   1.0000
  13.750   1.5994   0.02996   0.02420  -0.0303   0.0085   1.0000
  14.000   1.6045   0.03144   0.02576  -0.0284   0.0082   1.0000
  14.250   1.6067   0.03324   0.02766  -0.0265   0.0079   1.0000
  14.500   1.6038   0.03556   0.03009  -0.0245   0.0077   1.0000
  14.750   1.5932   0.03876   0.03344  -0.0225   0.0074   1.0000
  15.000   1.5848   0.04196   0.03678  -0.0212   0.0073   1.0000
  15.250   1.5832   0.04464   0.03958  -0.0204   0.0072   1.0000
  15.500   1.5794   0.04775   0.04281  -0.0200   0.0071   1.0000
  15.750   1.5728   0.05141   0.04659  -0.0200   0.0069   1.0000
  16.000   1.5631   0.05574   0.05106  -0.0206   0.0068   1.0000
  16.250   1.5504   0.06086   0.05632  -0.0218   0.0068   1.0000
  16.500   1.5330   0.06715   0.06277  -0.0240   0.0067   1.0000
  16.750   1.5116   0.07448   0.07027  -0.0269   0.0067   1.0000
  17.000   1.4845   0.08310   0.07907  -0.0306   0.0067   1.0000
  17.250   1.4531   0.09240   0.08854  -0.0344   0.0068   1.0000
  17.500   1.4186   0.10217   0.09846  -0.0384   0.0069   1.0000
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