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ARA-D 13% AIRFOIL (arad13-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: ARA-D 13% AIRFOIL (arad13-il)
Reynolds number: 50,000
Max Cl/Cd: 25.73 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-arad13-il-50000.txt
Download as CSV file: xf-arad13-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4216   0.12470   0.11780  -0.0056   1.0000   0.2171
  -9.000  -0.3725   0.11629   0.10934  -0.0020   1.0000   0.2247
  -8.750  -0.3789   0.11428   0.10741  -0.0037   1.0000   0.2338
  -8.500  -0.3769   0.11042   0.10364  -0.0045   1.0000   0.2391
  -8.250  -0.3639   0.10704   0.10029  -0.0040   1.0000   0.2509
  -8.000  -0.3711   0.10402   0.09738  -0.0053   1.0000   0.2581
  -7.750  -0.3621   0.10100   0.09442  -0.0048   1.0000   0.2714
  -7.500  -0.3540   0.09709   0.09059  -0.0045   1.0000   0.2805
  -7.250  -0.3771   0.09597   0.08962  -0.0054   1.0000   0.2929
  -7.000  -0.3477   0.09113   0.08479  -0.0035   1.0000   0.3065
  -6.750  -0.3475   0.08814   0.08192  -0.0025   1.0000   0.3213
  -6.500  -0.3502   0.08543   0.07933  -0.0017   1.0000   0.3386
  -6.250  -0.3466   0.08266   0.07665   0.0000   1.0000   0.3587
  -6.000  -0.3421   0.07997   0.07408   0.0022   1.0000   0.3799
  -5.750  -0.3402   0.07774   0.07196   0.0052   1.0000   0.4054
  -5.250  -0.3442   0.07408   0.06856   0.0142   1.0000   0.4671
  -5.000  -0.3380   0.07208   0.06666   0.0197   1.0000   0.5046
  -4.750  -0.2993   0.06924   0.06382   0.0252   1.0000   0.5816
  -4.500  -0.3327   0.04966   0.04216  -0.0304   1.0000   0.1972
  -4.250  -0.3176   0.04687   0.03914  -0.0306   1.0000   0.1966
  -4.000  -0.2995   0.04432   0.03622  -0.0312   1.0000   0.1969
  -3.750  -0.2804   0.04207   0.03363  -0.0317   1.0000   0.1997
  -3.500  -0.2636   0.04061   0.03216  -0.0313   1.0000   0.2046
  -3.250  -0.2420   0.03927   0.03054  -0.0318   1.0000   0.2107
  -3.000  -0.2171   0.03812   0.02880  -0.0328   1.0000   0.2170
  -2.750  -0.1980   0.03708   0.02788  -0.0329   1.0000   0.2248
  -2.500  -0.1418   0.03554   0.02597  -0.0390   0.9888   0.2405
  -2.250  -0.0852   0.03430   0.02452  -0.0450   0.9758   0.2602
  -2.000  -0.0307   0.03327   0.02340  -0.0504   0.9619   0.2844
  -1.750   0.0235   0.03237   0.02240  -0.0554   0.9472   0.3149
  -1.500   0.0786   0.03146   0.02159  -0.0602   0.9323   0.3548
  -1.250   0.1398   0.03019   0.02071  -0.0658   0.9185   0.4200
  -1.000   0.1888   0.02732   0.02025  -0.0667   0.9034   1.0000
  -0.750   0.2488   0.02739   0.01939  -0.0719   0.8852   1.0000
  -0.500   0.2968   0.02740   0.01903  -0.0748   0.8664   1.0000
  -0.250   0.3390   0.02743   0.01879  -0.0765   0.8472   1.0000
   0.000   0.3762   0.02747   0.01862  -0.0772   0.8278   1.0000
   0.250   0.4096   0.02754   0.01850  -0.0769   0.8082   1.0000
   0.500   0.4401   0.02763   0.01842  -0.0761   0.7884   1.0000
   0.750   0.4685   0.02773   0.01837  -0.0748   0.7686   1.0000
   1.000   0.4957   0.02782   0.01831  -0.0732   0.7486   1.0000
   1.250   0.5221   0.02792   0.01826  -0.0715   0.7286   1.0000
   1.500   0.5475   0.02805   0.01824  -0.0696   0.7082   1.0000
   1.750   0.5709   0.02840   0.01849  -0.0679   0.6856   1.0000
   2.000   0.5954   0.02865   0.01862  -0.0662   0.6637   1.0000
   2.250   0.6204   0.02888   0.01872  -0.0645   0.6422   1.0000
   2.500   0.6456   0.02909   0.01879  -0.0628   0.6210   1.0000
   2.750   0.6712   0.02932   0.01888  -0.0612   0.6004   1.0000
   3.000   0.6968   0.02961   0.01902  -0.0598   0.5802   1.0000
   3.250   0.7225   0.02994   0.01920  -0.0585   0.5605   1.0000
   3.500   0.7481   0.03038   0.01952  -0.0573   0.5414   1.0000
   3.750   0.7736   0.03092   0.01994  -0.0563   0.5228   1.0000
   4.000   0.7987   0.03156   0.02049  -0.0554   0.5049   1.0000
   4.250   0.8233   0.03236   0.02124  -0.0547   0.4878   1.0000
   4.500   0.8476   0.03327   0.02211  -0.0540   0.4717   1.0000
   4.750   0.8718   0.03422   0.02302  -0.0533   0.4569   1.0000
   5.000   0.8975   0.03503   0.02373  -0.0527   0.4442   1.0000
   5.250   0.9229   0.03587   0.02450  -0.0520   0.4314   1.0000
   5.500   0.9433   0.03745   0.02619  -0.0516   0.4183   1.0000
   5.750   0.9673   0.03860   0.02733  -0.0510   0.4079   1.0000
   6.000   0.9902   0.03986   0.02861  -0.0505   0.3971   1.0000
   6.250   1.0071   0.04192   0.03082  -0.0499   0.3869   1.0000
   6.500   1.0336   0.04279   0.03159  -0.0493   0.3781   1.0000
   6.750   1.0428   0.04581   0.03491  -0.0486   0.3691   1.0000
   7.000   1.0685   0.04677   0.03581  -0.0480   0.3610   1.0000
   7.250   1.0726   0.05032   0.03963  -0.0471   0.3534   1.0000
   7.500   1.0768   0.05371   0.04323  -0.0462   0.3463   1.0000
   7.750   1.1103   0.05403   0.04342  -0.0457   0.3398   1.0000
   8.000   1.0363   0.06584   0.05583  -0.0440   0.3360   1.0000
   8.250   0.8513   0.09513   0.08533  -0.0536   0.3435   1.0000
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