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ARA-D 13% AIRFOIL (arad13-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: ARA-D 13% AIRFOIL (arad13-il)
Reynolds number: 100,000
Max Cl/Cd: 41.81 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-arad13-il-100000.txt
Download as CSV file: xf-arad13-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3810   0.09771   0.09291  -0.0132   1.0000   0.1268
  -8.000  -0.4224   0.09359   0.08888  -0.0255   1.0000   0.1311
  -7.750  -0.4161   0.08846   0.08382  -0.0258   1.0000   0.1326
  -7.500  -0.3951   0.08570   0.08112  -0.0213   1.0000   0.1348
  -7.250  -0.3853   0.08267   0.07813  -0.0211   1.0000   0.1383
  -7.000  -0.4101   0.07686   0.07206  -0.0355   1.0000   0.1470
  -6.750  -0.3922   0.07329   0.06874  -0.0306   1.0000   0.1489
  -6.500  -0.3803   0.07130   0.06686  -0.0273   1.0000   0.1527
  -6.250  -0.4025   0.05255   0.04690  -0.0411   1.0000   0.1055
  -6.000  -0.3979   0.05072   0.04524  -0.0384   1.0000   0.1067
  -5.750  -0.3937   0.04770   0.04213  -0.0366   1.0000   0.1022
  -5.500  -0.3884   0.04401   0.03815  -0.0357   1.0000   0.1012
  -5.250  -0.3720   0.03980   0.03346  -0.0364   0.9987   0.1017
  -5.000  -0.3261   0.03413   0.02666  -0.0416   0.9928   0.1056
  -4.750  -0.2807   0.03267   0.02537  -0.0457   0.9846   0.1115
  -4.500  -0.2333   0.02980   0.02178  -0.0499   0.9770   0.1187
  -4.250  -0.1847   0.02850   0.02050  -0.0543   0.9695   0.1270
  -4.000  -0.1383   0.02674   0.01843  -0.0580   0.9602   0.1354
  -3.750  -0.0851   0.02551   0.01687  -0.0626   0.9540   0.1464
  -3.500  -0.0421   0.02424   0.01568  -0.0656   0.9426   0.1565
  -3.250   0.0026   0.02309   0.01442  -0.0685   0.9323   0.1686
  -3.000   0.0443   0.02217   0.01339  -0.0706   0.9204   0.1825
  -2.750   0.0783   0.02155   0.01274  -0.0712   0.9047   0.1969
  -2.500   0.1089   0.02087   0.01213  -0.0710   0.8885   0.2118
  -2.250   0.1370   0.02030   0.01160  -0.0703   0.8718   0.2282
  -2.000   0.1633   0.01979   0.01114  -0.0691   0.8549   0.2468
  -1.750   0.1887   0.01932   0.01071  -0.0677   0.8383   0.2686
  -1.500   0.2135   0.01883   0.01031  -0.0661   0.8224   0.2954
  -1.250   0.2380   0.01829   0.00996  -0.0646   0.8061   0.3337
  -1.000   0.2613   0.01735   0.00971  -0.0633   0.7893   0.4462
  -0.750   0.2950   0.01573   0.00946  -0.0614   0.7724   1.0000
  -0.500   0.3203   0.01583   0.00926  -0.0602   0.7556   1.0000
  -0.250   0.3459   0.01593   0.00912  -0.0591   0.7391   1.0000
   0.000   0.3717   0.01603   0.00898  -0.0581   0.7228   1.0000
   0.250   0.3978   0.01613   0.00886  -0.0571   0.7066   1.0000
   0.500   0.4242   0.01623   0.00876  -0.0562   0.6900   1.0000
   0.750   0.4509   0.01636   0.00871  -0.0555   0.6721   1.0000
   1.000   0.4777   0.01649   0.00868  -0.0548   0.6541   1.0000
   1.250   0.5047   0.01663   0.00865  -0.0541   0.6358   1.0000
   1.500   0.5317   0.01678   0.00864  -0.0535   0.6171   1.0000
   1.750   0.5589   0.01694   0.00864  -0.0530   0.5982   1.0000
   2.000   0.5860   0.01712   0.00865  -0.0524   0.5787   1.0000
   2.250   0.6131   0.01732   0.00867  -0.0519   0.5589   1.0000
   2.500   0.6403   0.01754   0.00873  -0.0514   0.5385   1.0000
   2.750   0.6673   0.01780   0.00887  -0.0510   0.5164   1.0000
   3.000   0.6943   0.01809   0.00901  -0.0506   0.4946   1.0000
   3.250   0.7213   0.01841   0.00918  -0.0502   0.4734   1.0000
   3.500   0.7482   0.01878   0.00938  -0.0499   0.4531   1.0000
   3.750   0.7750   0.01919   0.00962  -0.0496   0.4338   1.0000
   4.000   0.8018   0.01964   0.00993  -0.0493   0.4157   1.0000
   4.250   0.8286   0.02012   0.01028  -0.0491   0.3986   1.0000
   4.500   0.8553   0.02065   0.01070  -0.0489   0.3830   1.0000
   4.750   0.8820   0.02121   0.01115  -0.0487   0.3690   1.0000
   5.000   0.9088   0.02180   0.01157  -0.0485   0.3567   1.0000
   5.250   0.9354   0.02237   0.01209  -0.0483   0.3442   1.0000
   5.500   0.9618   0.02304   0.01275  -0.0482   0.3330   1.0000
   5.750   0.9889   0.02373   0.01322  -0.0481   0.3237   1.0000
   6.000   1.0145   0.02440   0.01400  -0.0479   0.3134   1.0000
   6.250   1.0416   0.02517   0.01459  -0.0478   0.3054   1.0000
   6.500   1.0667   0.02589   0.01546  -0.0476   0.2964   1.0000
   6.750   1.0940   0.02670   0.01605  -0.0476   0.2894   1.0000
   7.000   1.1180   0.02753   0.01710  -0.0472   0.2814   1.0000
   7.250   1.1443   0.02828   0.01777  -0.0471   0.2747   1.0000
   7.500   1.1691   0.02929   0.01883  -0.0469   0.2683   1.0000
   7.750   1.1929   0.03016   0.01982  -0.0465   0.2615   1.0000
   8.000   1.2200   0.03105   0.02054  -0.0466   0.2560   1.0000
   8.250   1.2415   0.03221   0.02194  -0.0460   0.2501   1.0000
   8.500   1.2644   0.03316   0.02301  -0.0455   0.2442   1.0000
   8.750   1.2912   0.03412   0.02381  -0.0456   0.2394   1.0000
   9.000   1.3102   0.03552   0.02549  -0.0448   0.2343   1.0000
   9.250   1.3304   0.03670   0.02684  -0.0441   0.2291   1.0000
   9.500   1.3548   0.03763   0.02773  -0.0438   0.2245   1.0000
   9.750   1.3753   0.03920   0.02938  -0.0433   0.2203   1.0000
  10.000   1.3888   0.04084   0.03137  -0.0419   0.2157   1.0000
  10.250   1.4079   0.04209   0.03272  -0.0412   0.2114   1.0000
  10.500   1.4335   0.04312   0.03364  -0.0412   0.2076   1.0000
  10.750   1.4429   0.04532   0.03615  -0.0396   0.2040   1.0000
  11.000   1.4468   0.04760   0.03879  -0.0374   0.2002   1.0000
  11.250   1.4601   0.04924   0.04056  -0.0362   0.1966   1.0000
  11.500   1.4821   0.05031   0.04159  -0.0358   0.1932   1.0000
  11.750   1.4959   0.05248   0.04384  -0.0349   0.1902   1.0000
  12.000   1.4737   0.05615   0.04801  -0.0307   0.1879   1.0000
  12.250   1.4442   0.06018   0.05242  -0.0262   0.1860   1.0000
  12.500   1.3926   0.06566   0.05822  -0.0214   0.1851   1.0000
  13.250   1.4527   0.06952   0.06203  -0.0201   0.1763   1.0000
  13.500   0.8861   0.17731   0.17075  -0.0754   0.2241   1.0000
  13.750   0.9256   0.18159   0.17509  -0.0730   0.2224   1.0000
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