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AIRFOIL PROFILE12A 9.00% (rg12a-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: AIRFOIL PROFILE12A 9.00% (rg12a-il)
Reynolds number: 100,000
Max Cl/Cd: 50.78 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg12a-il-100000.txt
Download as CSV file: xf-rg12a-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AIRFOIL PROFILE12A 9.00%                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4733   0.10861   0.10347  -0.0200   1.0000   0.0886
  -9.500  -0.4866   0.10573   0.10069  -0.0246   1.0000   0.0914
  -9.250  -0.5076   0.10267   0.09780  -0.0305   1.0000   0.0921
  -9.000  -0.4790   0.09752   0.09257  -0.0246   1.0000   0.0952
  -8.750  -0.4728   0.09438   0.08946  -0.0240   1.0000   0.0985
  -8.500  -0.3863   0.08150   0.07694  -0.0271   1.0000   0.1144
  -8.250  -0.4069   0.07775   0.07329  -0.0301   1.0000   0.1185
  -8.000  -0.4293   0.07387   0.06951  -0.0328   1.0000   0.1191
  -7.750  -0.4048   0.07011   0.06575  -0.0284   1.0000   0.1265
  -7.500  -0.4221   0.06656   0.06230  -0.0292   1.0000   0.1303
  -7.250  -0.4458   0.06258   0.05839  -0.0313   1.0000   0.1317
  -7.000  -0.4797   0.05843   0.05410  -0.0349   1.0000   0.1335
  -6.750  -0.5136   0.06598   0.06140  -0.0327   1.0000   0.1305
  -6.500  -0.5137   0.06224   0.05764  -0.0326   1.0000   0.1379
  -6.250  -0.5136   0.05895   0.05423  -0.0328   1.0000   0.1501
  -5.750  -0.4968   0.05314   0.04840  -0.0302   1.0000   0.1703
  -5.500  -0.4780   0.03983   0.03328  -0.0344   1.0000   0.0800
  -5.250  -0.4578   0.03454   0.02748  -0.0329   1.0000   0.0626
  -5.000  -0.4384   0.03066   0.02314  -0.0317   1.0000   0.0580
  -4.750  -0.4153   0.02729   0.01894  -0.0301   1.0000   0.0543
  -4.500  -0.3922   0.02499   0.01627  -0.0289   1.0000   0.0543
  -4.250  -0.3693   0.02309   0.01419  -0.0279   1.0000   0.0567
  -4.000  -0.3461   0.02186   0.01275  -0.0268   1.0000   0.0630
  -3.750  -0.3224   0.02013   0.01091  -0.0256   1.0000   0.0679
  -3.500  -0.2991   0.01896   0.00967  -0.0244   1.0000   0.0784
  -3.250  -0.2768   0.01751   0.00846  -0.0235   1.0000   0.1038
  -3.000  -0.2548   0.01583   0.00736  -0.0227   1.0000   0.1861
  -2.750  -0.2423   0.01317   0.00706  -0.0202   1.0000   0.5903
  -2.500  -0.2408   0.01320   0.00759  -0.0128   1.0000   0.8000
  -2.250  -0.2360   0.01332   0.00773  -0.0067   1.0000   0.8703
  -2.000  -0.2141   0.01345   0.00778  -0.0037   1.0000   0.9418
  -1.750  -0.0928   0.01388   0.00758  -0.0204   1.0000   1.0000
  -1.500  -0.0980   0.01373   0.00738  -0.0160   1.0000   1.0000
  -1.250  -0.0996   0.01365   0.00721  -0.0123   1.0000   1.0000
  -1.000  -0.0911   0.01370   0.00714  -0.0103   1.0000   1.0000
  -0.750  -0.0763   0.01387   0.00718  -0.0094   1.0000   1.0000
  -0.500  -0.0334   0.01433   0.00745  -0.0135   0.9923   1.0000
  -0.250   0.0185   0.01479   0.00776  -0.0191   0.9811   1.0000
   0.000   0.0706   0.01516   0.00802  -0.0245   0.9701   1.0000
   0.250   0.1198   0.01536   0.00812  -0.0292   0.9576   1.0000
   0.500   0.1676   0.01546   0.00817  -0.0335   0.9446   1.0000
   0.750   0.2148   0.01548   0.00816  -0.0374   0.9315   1.0000
   1.000   0.2623   0.01542   0.00809  -0.0413   0.9183   1.0000
   1.250   0.3106   0.01526   0.00795  -0.0451   0.9052   1.0000
   1.500   0.3607   0.01498   0.00773  -0.0490   0.8922   1.0000
   1.750   0.4079   0.01466   0.00746  -0.0521   0.8780   1.0000
   2.000   0.4529   0.01432   0.00717  -0.0547   0.8624   1.0000
   2.250   0.4960   0.01396   0.00689  -0.0568   0.8454   1.0000
   2.500   0.5262   0.01382   0.00678  -0.0566   0.8222   1.0000
   2.750   0.5582   0.01368   0.00664  -0.0566   0.7993   1.0000
   3.000   0.5881   0.01360   0.00655  -0.0562   0.7748   1.0000
   3.250   0.6136   0.01366   0.00661  -0.0550   0.7477   1.0000
   3.500   0.6386   0.01376   0.00668  -0.0538   0.7195   1.0000
   3.750   0.6630   0.01393   0.00679  -0.0526   0.6906   1.0000
   4.000   0.6866   0.01414   0.00695  -0.0512   0.6603   1.0000
   4.250   0.7090   0.01439   0.00720  -0.0497   0.6282   1.0000
   4.500   0.7315   0.01466   0.00742  -0.0483   0.5952   1.0000
   4.750   0.7540   0.01497   0.00763  -0.0468   0.5619   1.0000
   5.000   0.7752   0.01530   0.00794  -0.0452   0.5253   1.0000
   5.250   0.7963   0.01568   0.00828  -0.0436   0.4879   1.0000
   5.500   0.8167   0.01612   0.00861  -0.0420   0.4486   1.0000
   5.750   0.8361   0.01662   0.00901  -0.0403   0.4061   1.0000
   6.000   0.8548   0.01720   0.00951  -0.0386   0.3603   1.0000
   6.250   0.8725   0.01792   0.01008  -0.0368   0.3114   1.0000
   6.500   0.8881   0.01876   0.01074  -0.0348   0.2557   1.0000
   6.750   0.9024   0.01981   0.01147  -0.0329   0.1970   1.0000
   7.000   0.9156   0.02132   0.01263  -0.0309   0.1425   1.0000
   7.250   0.9272   0.02340   0.01437  -0.0285   0.1019   1.0000
   7.500   0.9434   0.02523   0.01613  -0.0266   0.0797   1.0000
   7.750   0.9632   0.02725   0.01815  -0.0253   0.0694   1.0000
   8.000   0.9871   0.03002   0.02074  -0.0249   0.0630   1.0000
   8.250   1.0108   0.03207   0.02321  -0.0238   0.0592   1.0000
   8.500   1.0315   0.03403   0.02537  -0.0228   0.0546   1.0000
   8.750   1.0533   0.03742   0.02884  -0.0224   0.0516   1.0000
   9.000   1.0693   0.04128   0.03312  -0.0209   0.0507   1.0000
   9.250   1.0803   0.04472   0.03708  -0.0188   0.0503   1.0000
   9.500   1.0868   0.04852   0.04138  -0.0166   0.0502   1.0000
   9.750   1.0880   0.05214   0.04548  -0.0140   0.0498   1.0000
  10.000   1.0837   0.05577   0.04957  -0.0113   0.0493   1.0000
  10.250   1.0752   0.05961   0.05378  -0.0087   0.0491   1.0000
  10.500   1.0610   0.06338   0.05787  -0.0061   0.0491   1.0000
  10.750   1.0435   0.06714   0.06184  -0.0036   0.0494   1.0000
  11.000   1.0251   0.07125   0.06613  -0.0023   0.0497   1.0000
  11.250   1.0075   0.07605   0.07107  -0.0023   0.0502   1.0000
  11.500   0.9311   0.08792   0.08344  -0.0106   0.0577   1.0000
  11.750   0.9027   0.09771   0.09328  -0.0175   0.0600   1.0000
  12.000   0.8905   0.10556   0.10111  -0.0216   0.0616   1.0000
  12.250   0.8936   0.11071   0.10626  -0.0217   0.0628   1.0000
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