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ARA-D 10% AIRFOIL (arad10-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: ARA-D 10% AIRFOIL (arad10-il)
Reynolds number: 500,000
Max Cl/Cd: 82.3 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-arad10-il-500000-n5.txt
Download as CSV file: xf-arad10-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ARA-D 10% AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.7490   0.03061   0.02669  -0.0720   1.0000   0.0128
 -10.250  -0.7292   0.02763   0.02337  -0.0731   1.0000   0.0130
 -10.000  -0.7070   0.02559   0.02106  -0.0736   1.0000   0.0131
  -9.750  -0.6843   0.02388   0.01913  -0.0739   1.0000   0.0133
  -9.500  -0.6613   0.02249   0.01762  -0.0739   1.0000   0.0136
  -9.250  -0.6381   0.02144   0.01646  -0.0736   1.0000   0.0138
  -9.000  -0.6155   0.02053   0.01545  -0.0730   1.0000   0.0140
  -8.750  -0.5847   0.01955   0.01433  -0.0742   0.9976   0.0143
  -8.500  -0.5524   0.01863   0.01328  -0.0755   0.9952   0.0146
  -8.250  -0.5201   0.01777   0.01230  -0.0768   0.9924   0.0149
  -8.000  -0.4884   0.01699   0.01139  -0.0778   0.9883   0.0153
  -7.750  -0.4558   0.01627   0.01056  -0.0790   0.9848   0.0156
  -7.500  -0.4239   0.01564   0.00980  -0.0799   0.9802   0.0160
  -7.250  -0.3926   0.01498   0.00907  -0.0808   0.9749   0.0164
  -7.000  -0.3606   0.01445   0.00849  -0.0817   0.9700   0.0170
  -6.750  -0.3309   0.01400   0.00798  -0.0820   0.9626   0.0175
  -6.250  -0.2720   0.01321   0.00704  -0.0824   0.9472   0.0190
  -6.000  -0.2435   0.01283   0.00662  -0.0823   0.9391   0.0200
  -5.750  -0.2155   0.01252   0.00626  -0.0822   0.9293   0.0213
  -5.500  -0.1875   0.01223   0.00591  -0.0819   0.9200   0.0227
  -5.250  -0.1597   0.01192   0.00558  -0.0817   0.9096   0.0243
  -5.000  -0.1316   0.01168   0.00527  -0.0815   0.8990   0.0264
  -4.750  -0.1036   0.01143   0.00500  -0.0812   0.8881   0.0288
  -4.500  -0.0754   0.01123   0.00475  -0.0810   0.8763   0.0316
  -4.250  -0.0470   0.01104   0.00453  -0.0809   0.8642   0.0348
  -4.000  -0.0186   0.01087   0.00433  -0.0808   0.8520   0.0384
  -3.750   0.0098   0.01074   0.00413  -0.0806   0.8393   0.0421
  -3.500   0.0385   0.01059   0.00395  -0.0806   0.8260   0.0459
  -3.250   0.0673   0.01046   0.00378  -0.0805   0.8124   0.0498
  -3.000   0.0961   0.01036   0.00363  -0.0805   0.7989   0.0549
  -2.750   0.1249   0.01025   0.00350  -0.0805   0.7846   0.0608
  -2.500   0.1535   0.01018   0.00337  -0.0804   0.7658   0.0664
  -2.250   0.1817   0.01017   0.00324  -0.0802   0.7394   0.0725
  -2.000   0.2102   0.01015   0.00314  -0.0801   0.7113   0.0797
  -1.500   0.2677   0.01015   0.00298  -0.0801   0.6683   0.0956
  -1.250   0.2966   0.01014   0.00292  -0.0802   0.6480   0.1044
  -1.000   0.3256   0.01015   0.00288  -0.0802   0.6289   0.1135
  -0.750   0.3546   0.01016   0.00285  -0.0803   0.6114   0.1233
  -0.500   0.3835   0.01019   0.00283  -0.0804   0.5926   0.1337
  -0.250   0.4123   0.01024   0.00281  -0.0805   0.5723   0.1441
   0.000   0.4412   0.01029   0.00281  -0.0806   0.5529   0.1565
   0.250   0.4700   0.01033   0.00283  -0.0807   0.5327   0.1715
   0.500   0.4987   0.01040   0.00285  -0.0808   0.5086   0.1885
   0.750   0.5273   0.01049   0.00289  -0.0809   0.4834   0.2087
   1.000   0.5558   0.01056   0.00294  -0.0810   0.4586   0.2384
   1.250   0.5842   0.01062   0.00302  -0.0812   0.4307   0.2897
   1.750   0.6312   0.00922   0.00312  -0.0794   0.3706   1.0000
   2.000   0.6592   0.00952   0.00323  -0.0794   0.3407   1.0000
   2.250   0.6871   0.00983   0.00337  -0.0795   0.3121   1.0000
   2.500   0.7150   0.01014   0.00351  -0.0795   0.2879   1.0000
   2.750   0.7431   0.01040   0.00366  -0.0795   0.2699   1.0000
   3.000   0.7711   0.01066   0.00381  -0.0796   0.2546   1.0000
   3.500   0.8271   0.01115   0.00412  -0.0796   0.2283   1.0000
   3.750   0.8551   0.01138   0.00429  -0.0797   0.2184   1.0000
   4.000   0.8828   0.01164   0.00447  -0.0797   0.2082   1.0000
   4.250   0.9107   0.01186   0.00465  -0.0797   0.2001   1.0000
   4.500   0.9383   0.01212   0.00484  -0.0797   0.1924   1.0000
   4.750   0.9660   0.01234   0.00504  -0.0797   0.1854   1.0000
   5.000   0.9933   0.01261   0.00525  -0.0796   0.1784   1.0000
   5.250   1.0209   0.01283   0.00546  -0.0796   0.1734   1.0000
   5.500   1.0482   0.01308   0.00568  -0.0795   0.1678   1.0000
   5.750   1.0750   0.01337   0.00593  -0.0794   0.1622   1.0000
   6.000   1.1023   0.01360   0.00616  -0.0793   0.1575   1.0000
   6.250   1.1291   0.01387   0.00642  -0.0792   0.1527   1.0000
   6.500   1.1554   0.01419   0.00670  -0.0791   0.1479   1.0000
   6.750   1.1823   0.01443   0.00696  -0.0789   0.1440   1.0000
   7.000   1.2086   0.01471   0.00724  -0.0787   0.1393   1.0000
   7.250   1.2344   0.01505   0.00755  -0.0785   0.1349   1.0000
   7.500   1.2605   0.01533   0.00785  -0.0783   0.1313   1.0000
   7.750   1.2863   0.01563   0.00817  -0.0780   0.1269   1.0000
   8.000   1.3115   0.01599   0.00850  -0.0777   0.1228   1.0000
   8.250   1.3367   0.01633   0.00886  -0.0774   0.1193   1.0000
   8.500   1.3618   0.01665   0.00921  -0.0770   0.1155   1.0000
   8.750   1.3863   0.01703   0.00958  -0.0766   0.1116   1.0000
   9.000   1.4101   0.01745   0.01000  -0.0761   0.1081   1.0000
   9.250   1.4344   0.01779   0.01039  -0.0756   0.1050   1.0000
   9.500   1.4580   0.01819   0.01081  -0.0751   0.1014   1.0000
   9.750   1.4806   0.01865   0.01127  -0.0744   0.0980   1.0000
  10.000   1.5032   0.01909   0.01175  -0.0737   0.0952   1.0000
  10.250   1.5256   0.01951   0.01221  -0.0729   0.0922   1.0000
  10.500   1.5469   0.01999   0.01271  -0.0721   0.0890   1.0000
  10.750   1.5668   0.02056   0.01329  -0.0710   0.0858   1.0000
  11.000   1.5875   0.02102   0.01381  -0.0700   0.0836   1.0000
  11.250   1.6071   0.02154   0.01437  -0.0689   0.0810   1.0000
  11.500   1.6252   0.02212   0.01499  -0.0675   0.0783   1.0000
  11.750   1.6414   0.02280   0.01569  -0.0659   0.0757   1.0000
  12.000   1.6583   0.02338   0.01634  -0.0644   0.0740   1.0000
  12.250   1.6728   0.02401   0.01705  -0.0624   0.0721   1.0000
  12.500   1.6842   0.02475   0.01785  -0.0601   0.0701   1.0000
  12.750   1.6947   0.02561   0.01875  -0.0577   0.0681   1.0000
  13.000   1.7044   0.02660   0.01978  -0.0555   0.0661   1.0000
  13.250   1.7165   0.02746   0.02074  -0.0536   0.0646   1.0000
  13.500   1.7274   0.02846   0.02182  -0.0518   0.0629   1.0000
  13.750   1.7372   0.02958   0.02301  -0.0500   0.0611   1.0000
  14.000   1.7453   0.03088   0.02436  -0.0482   0.0592   1.0000
  14.250   1.7527   0.03230   0.02585  -0.0466   0.0575   1.0000
  14.500   1.7619   0.03364   0.02729  -0.0452   0.0558   1.0000
  14.750   1.7691   0.03518   0.02892  -0.0438   0.0541   1.0000
  15.000   1.7745   0.03696   0.03076  -0.0426   0.0524   1.0000
  15.250   1.7779   0.03901   0.03289  -0.0414   0.0509   1.0000
  15.500   1.7820   0.04107   0.03504  -0.0405   0.0496   1.0000
  15.750   1.7860   0.04321   0.03729  -0.0397   0.0482   1.0000
  16.000   1.7879   0.04565   0.03983  -0.0391   0.0468   1.0000
  16.250   1.7876   0.04843   0.04271  -0.0387   0.0455   1.0000
  16.500   1.7848   0.05161   0.04597  -0.0385   0.0444   1.0000
  16.750   1.7802   0.05509   0.04956  -0.0385   0.0434   1.0000
  17.000   1.7777   0.05843   0.05304  -0.0387   0.0426   1.0000
  17.250   1.7731   0.06218   0.05691  -0.0391   0.0418   1.0000
  17.500   1.7663   0.06633   0.06119  -0.0399   0.0410   1.0000
  17.750   1.7569   0.07097   0.06595  -0.0409   0.0401   1.0000
  18.000   1.7446   0.07618   0.07129  -0.0423   0.0394   1.0000
  18.250   1.7293   0.08200   0.07724  -0.0441   0.0387   1.0000
  18.500   1.7109   0.08843   0.08381  -0.0464   0.0381   1.0000
  18.750   1.6898   0.09548   0.09099  -0.0490   0.0375   1.0000
  19.000   1.6724   0.10203   0.09769  -0.0516   0.0371   1.0000
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