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ARA-D 13% AIRFOIL (arad13-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: ARA-D 13% AIRFOIL (arad13-il)
Reynolds number: 200,000
Max Cl/Cd: 56.07 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-arad13-il-200000.txt
Download as CSV file: xf-arad13-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ARA-D 13% 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3013   0.09380   0.09051  -0.0203   1.0000   0.0731
  -8.750  -0.3466   0.08513   0.08189  -0.0298   1.0000   0.0756
  -8.500  -0.5324   0.05831   0.05443  -0.0449   1.0000   0.0488
  -8.250  -0.5199   0.05600   0.05212  -0.0449   1.0000   0.0491
  -8.000  -0.5196   0.04873   0.04456  -0.0469   1.0000   0.0477
  -7.750  -0.5323   0.03456   0.02913  -0.0496   1.0000   0.0471
  -7.500  -0.5180   0.02918   0.02277  -0.0497   1.0000   0.0491
  -7.250  -0.4945   0.02878   0.02258  -0.0491   1.0000   0.0505
  -7.000  -0.4754   0.02730   0.02092  -0.0481   1.0000   0.0522
  -6.750  -0.4612   0.02513   0.01817  -0.0462   1.0000   0.0543
  -6.500  -0.4519   0.02433   0.01740  -0.0436   1.0000   0.0557
  -6.250  -0.4102   0.02345   0.01645  -0.0466   0.9950   0.0592
  -6.000  -0.3683   0.02222   0.01507  -0.0496   0.9894   0.0631
  -5.750  -0.3248   0.02124   0.01378  -0.0527   0.9839   0.0679
  -5.500  -0.2831   0.02042   0.01311  -0.0557   0.9769   0.0723
  -5.250  -0.2416   0.01948   0.01204  -0.0583   0.9689   0.0776
  -5.000  -0.2035   0.01896   0.01146  -0.0602   0.9566   0.0829
  -4.750  -0.1689   0.01829   0.01080  -0.0613   0.9423   0.0880
  -4.500  -0.1378   0.01793   0.01030  -0.0614   0.9258   0.0936
  -4.250  -0.1108   0.01741   0.00983  -0.0607   0.9084   0.0987
  -4.000  -0.0845   0.01718   0.00945  -0.0597   0.8908   0.1048
  -3.750  -0.0591   0.01672   0.00904  -0.0587   0.8738   0.1107
  -3.500  -0.0328   0.01656   0.00871  -0.0577   0.8571   0.1178
  -3.250  -0.0070   0.01612   0.00834  -0.0568   0.8410   0.1253
  -3.000   0.0195   0.01581   0.00793  -0.0560   0.8247   0.1341
  -2.750   0.0468   0.01560   0.00769  -0.0554   0.8074   0.1438
  -2.500   0.0742   0.01526   0.00736  -0.0549   0.7905   0.1541
  -2.250   0.1021   0.01501   0.00706  -0.0545   0.7743   0.1660
  -2.000   0.1301   0.01485   0.00685  -0.0541   0.7589   0.1790
  -1.750   0.1580   0.01458   0.00659  -0.0538   0.7441   0.1935
  -1.500   0.1862   0.01435   0.00636  -0.0535   0.7290   0.2101
  -1.250   0.2148   0.01411   0.00616  -0.0534   0.7132   0.2301
  -1.000   0.2434   0.01387   0.00597  -0.0533   0.6980   0.2561
  -0.750   0.2716   0.01350   0.00579  -0.0533   0.6832   0.3003
  -0.500   0.2950   0.01215   0.00572  -0.0525   0.6695   0.6306
  -0.250   0.3257   0.01113   0.00544  -0.0510   0.6537   1.0000
   0.000   0.3539   0.01122   0.00534  -0.0508   0.6378   1.0000
   0.250   0.3821   0.01133   0.00528  -0.0506   0.6220   1.0000
   0.500   0.4104   0.01144   0.00523  -0.0505   0.6065   1.0000
   0.750   0.4387   0.01158   0.00520  -0.0503   0.5909   1.0000
   1.000   0.4671   0.01172   0.00517  -0.0502   0.5749   1.0000
   1.250   0.4955   0.01187   0.00517  -0.0501   0.5580   1.0000
   1.500   0.5240   0.01202   0.00519  -0.0500   0.5404   1.0000
   1.750   0.5525   0.01218   0.00523  -0.0500   0.5224   1.0000
   2.000   0.5808   0.01237   0.00528  -0.0499   0.5037   1.0000
   2.250   0.6090   0.01258   0.00534  -0.0499   0.4841   1.0000
   2.500   0.6373   0.01279   0.00544  -0.0498   0.4636   1.0000
   2.750   0.6655   0.01303   0.00556  -0.0498   0.4425   1.0000
   3.000   0.6934   0.01330   0.00569  -0.0498   0.4209   1.0000
   3.250   0.7212   0.01360   0.00585  -0.0498   0.3998   1.0000
   3.500   0.7488   0.01394   0.00604  -0.0497   0.3799   1.0000
   3.750   0.7762   0.01431   0.00626  -0.0497   0.3615   1.0000
   4.000   0.8037   0.01468   0.00652  -0.0496   0.3444   1.0000
   4.250   0.8310   0.01507   0.00680  -0.0496   0.3290   1.0000
   4.500   0.8583   0.01549   0.00711  -0.0496   0.3155   1.0000
   4.750   0.8851   0.01596   0.00744  -0.0495   0.3037   1.0000
   5.000   0.9122   0.01636   0.00778  -0.0495   0.2924   1.0000
   5.250   0.9392   0.01680   0.00817  -0.0494   0.2824   1.0000
   5.500   0.9658   0.01729   0.00855  -0.0493   0.2736   1.0000
   5.750   0.9927   0.01772   0.00897  -0.0492   0.2651   1.0000
   6.000   1.0191   0.01820   0.00936  -0.0491   0.2574   1.0000
   6.250   1.0456   0.01870   0.00985  -0.0490   0.2504   1.0000
   6.500   1.0720   0.01912   0.01027  -0.0489   0.2436   1.0000
   6.750   1.0978   0.01977   0.01079  -0.0487   0.2375   1.0000
   7.000   1.1240   0.02016   0.01127  -0.0485   0.2314   1.0000
   7.250   1.1497   0.02065   0.01173  -0.0483   0.2259   1.0000
   7.500   1.1751   0.02132   0.01234  -0.0482   0.2207   1.0000
   7.750   1.2005   0.02176   0.01287  -0.0479   0.2154   1.0000
   8.000   1.2256   0.02227   0.01336  -0.0476   0.2106   1.0000
   8.250   1.2506   0.02308   0.01406  -0.0475   0.2060   1.0000
   8.500   1.2748   0.02353   0.01466  -0.0470   0.2015   1.0000
   8.750   1.2989   0.02405   0.01522  -0.0467   0.1969   1.0000
   9.000   1.3231   0.02469   0.01581  -0.0463   0.1930   1.0000
   9.250   1.3468   0.02549   0.01664  -0.0460   0.1891   1.0000
   9.500   1.3693   0.02605   0.01733  -0.0454   0.1849   1.0000
   9.750   1.3920   0.02663   0.01794  -0.0448   0.1810   1.0000
  10.000   1.4154   0.02741   0.01863  -0.0445   0.1775   1.0000
  10.250   1.4369   0.02827   0.01960  -0.0439   0.1741   1.0000
  10.500   1.4569   0.02894   0.02042  -0.0429   0.1705   1.0000
  10.750   1.4774   0.02960   0.02112  -0.0422   0.1671   1.0000
  11.000   1.4989   0.03035   0.02182  -0.0416   0.1640   1.0000
  11.250   1.5198   0.03145   0.02296  -0.0410   0.1609   1.0000
  11.500   1.5351   0.03227   0.02398  -0.0395   0.1579   1.0000
  11.750   1.5514   0.03307   0.02488  -0.0382   0.1548   1.0000
  12.000   1.5689   0.03382   0.02566  -0.0372   0.1521   1.0000
  12.250   1.5904   0.03484   0.02659  -0.0368   0.1494   1.0000
  12.500   1.6024   0.03604   0.02796  -0.0351   0.1470   1.0000
  12.750   1.6093   0.03711   0.02924  -0.0326   0.1445   1.0000
  13.000   1.6165   0.03816   0.03042  -0.0303   0.1421   1.0000
  13.250   1.6252   0.03916   0.03148  -0.0282   0.1399   1.0000
  13.500   1.6393   0.04014   0.03243  -0.0269   0.1378   1.0000
  13.750   1.6561   0.04163   0.03392  -0.0262   0.1354   1.0000
  14.000   1.6504   0.04334   0.03589  -0.0231   0.1338   1.0000
  14.250   1.6469   0.04526   0.03802  -0.0209   0.1320   1.0000
  14.500   1.6470   0.04715   0.04008  -0.0193   0.1300   1.0000
  14.750   1.6511   0.04888   0.04189  -0.0181   0.1282   1.0000
  15.000   1.6611   0.05025   0.04328  -0.0173   0.1263   1.0000
  15.250   1.6807   0.05142   0.04436  -0.0169   0.1241   1.0000
  15.500   1.6696   0.05450   0.04769  -0.0157   0.1228   1.0000
  15.750   1.6555   0.05804   0.05149  -0.0149   0.1214   1.0000
  16.000   1.6412   0.06191   0.05560  -0.0147   0.1200   1.0000
  16.250   1.6293   0.06579   0.05968  -0.0149   0.1185   1.0000
  16.500   1.6222   0.06926   0.06328  -0.0153   0.1170   1.0000
  16.750   1.6246   0.07170   0.06577  -0.0155   0.1154   1.0000
  17.000   1.6431   0.07237   0.06635  -0.0149   0.1136   1.0000
  17.250   1.6336   0.07653   0.07064  -0.0155   0.1122   1.0000
  17.500   1.5931   0.08458   0.07903  -0.0182   0.1114   1.0000
  17.750   1.5368   0.09599   0.09081  -0.0234   0.1107   1.0000
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