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ARA-D 10% AIRFOIL (arad10-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: ARA-D 10% AIRFOIL (arad10-il)
Reynolds number: 200,000
Max Cl/Cd: 66.2 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-arad10-il-200000.txt
Download as CSV file: xf-arad10-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3685   0.10291   0.09925  -0.0214   1.0000   0.0542
  -8.500  -0.3887   0.09934   0.09578  -0.0286   1.0000   0.0552
  -8.250  -0.3926   0.09512   0.09162  -0.0307   1.0000   0.0555
  -8.000  -0.3761   0.09221   0.08872  -0.0268   1.0000   0.0562
  -7.750  -0.3693   0.08966   0.08620  -0.0257   1.0000   0.0570
  -7.500  -0.3669   0.08710   0.08369  -0.0255   1.0000   0.0578
  -7.250  -0.3672   0.08447   0.08112  -0.0258   1.0000   0.0589
  -7.000  -0.3696   0.08175   0.07845  -0.0263   1.0000   0.0601
  -6.750  -0.3740   0.07868   0.07541  -0.0280   1.0000   0.0619
  -6.500  -0.3776   0.07123   0.06782  -0.0396   1.0000   0.0642
  -6.250  -0.3760   0.06916   0.06582  -0.0363   1.0000   0.0646
  -6.000  -0.3729   0.06734   0.06405  -0.0338   1.0000   0.0652
  -5.750  -0.3629   0.06512   0.06184  -0.0332   0.9993   0.0663
  -5.500  -0.3113   0.03991   0.03547  -0.0560   0.9959   0.0484
  -5.250  -0.2724   0.03195   0.02678  -0.0617   0.9936   0.0470
  -5.000  -0.2339   0.02569   0.01954  -0.0656   0.9904   0.0471
  -4.750  -0.1943   0.02272   0.01603  -0.0685   0.9871   0.0491
  -4.500  -0.1526   0.02178   0.01499  -0.0715   0.9840   0.0526
  -4.250  -0.1130   0.02035   0.01328  -0.0740   0.9796   0.0574
  -4.000  -0.0720   0.01942   0.01214  -0.0765   0.9750   0.0629
  -3.750  -0.0292   0.01867   0.01139  -0.0796   0.9719   0.0700
  -3.500   0.0110   0.01794   0.01061  -0.0821   0.9668   0.0777
  -3.250   0.0523   0.01726   0.00983  -0.0847   0.9618   0.0865
  -3.000   0.0961   0.01681   0.00935  -0.0878   0.9583   0.0957
  -2.750   0.1347   0.01615   0.00875  -0.0898   0.9521   0.1045
  -2.500   0.1721   0.01555   0.00812  -0.0915   0.9447   0.1142
  -2.250   0.2083   0.01522   0.00776  -0.0927   0.9369   0.1250
  -2.000   0.2406   0.01471   0.00733  -0.0932   0.9269   0.1366
  -1.750   0.2698   0.01432   0.00696  -0.0930   0.9145   0.1490
  -1.500   0.2973   0.01394   0.00658  -0.0921   0.8997   0.1626
  -1.250   0.3231   0.01362   0.00625  -0.0908   0.8826   0.1773
  -1.000   0.3489   0.01333   0.00596  -0.0896   0.8658   0.1935
  -0.750   0.3753   0.01303   0.00571  -0.0888   0.8500   0.2120
  -0.500   0.4019   0.01275   0.00550  -0.0880   0.8339   0.2342
  -0.250   0.4288   0.01247   0.00530  -0.0874   0.8173   0.2647
   0.000   0.4558   0.01201   0.00514  -0.0869   0.8006   0.3379
   0.250   0.4749   0.01012   0.00485  -0.0840   0.7847   1.0000
   0.500   0.5026   0.01020   0.00473  -0.0835   0.7673   1.0000
   0.750   0.5302   0.01030   0.00465  -0.0830   0.7494   1.0000
   1.000   0.5579   0.01041   0.00460  -0.0825   0.7308   1.0000
   1.250   0.5855   0.01053   0.00458  -0.0821   0.7118   1.0000
   1.500   0.6132   0.01067   0.00457  -0.0817   0.6924   1.0000
   1.750   0.6407   0.01082   0.00457  -0.0813   0.6722   1.0000
   2.000   0.6682   0.01098   0.00461  -0.0809   0.6500   1.0000
   2.250   0.6957   0.01116   0.00465  -0.0806   0.6270   1.0000
   2.500   0.7228   0.01136   0.00471  -0.0802   0.6026   1.0000
   2.750   0.7499   0.01157   0.00478  -0.0798   0.5747   1.0000
   3.000   0.7767   0.01182   0.00488  -0.0794   0.5442   1.0000
   3.250   0.8030   0.01213   0.00500  -0.0789   0.5097   1.0000
   3.500   0.8287   0.01252   0.00516  -0.0784   0.4700   1.0000
   3.750   0.8540   0.01297   0.00537  -0.0779   0.4253   1.0000
   4.000   0.8788   0.01352   0.00565  -0.0774   0.3828   1.0000
   4.250   0.9036   0.01409   0.00599  -0.0770   0.3473   1.0000
   4.500   0.9283   0.01470   0.00636  -0.0765   0.3208   1.0000
   4.750   0.9537   0.01524   0.00677  -0.0762   0.3001   1.0000
   5.000   0.9790   0.01578   0.00718  -0.0758   0.2837   1.0000
   5.250   1.0041   0.01635   0.00762  -0.0754   0.2701   1.0000
   5.500   1.0294   0.01687   0.00807  -0.0750   0.2582   1.0000
   5.750   1.0551   0.01735   0.00853  -0.0747   0.2477   1.0000
   6.000   1.0798   0.01796   0.00903  -0.0743   0.2386   1.0000
   6.250   1.1054   0.01839   0.00949  -0.0740   0.2297   1.0000
   6.500   1.1301   0.01904   0.01005  -0.0735   0.2224   1.0000
   6.750   1.1554   0.01948   0.01053  -0.0731   0.2147   1.0000
   7.000   1.1796   0.02020   0.01113  -0.0727   0.2079   1.0000
   7.250   1.2046   0.02061   0.01165  -0.0723   0.2012   1.0000
   7.500   1.2288   0.02120   0.01219  -0.0718   0.1952   1.0000
   7.750   1.2529   0.02185   0.01287  -0.0713   0.1893   1.0000
   8.000   1.2769   0.02235   0.01343  -0.0708   0.1832   1.0000
   8.250   1.3005   0.02317   0.01414  -0.0703   0.1779   1.0000
   8.500   1.3238   0.02370   0.01482  -0.0696   0.1727   1.0000
   8.750   1.3466   0.02425   0.01541  -0.0690   0.1675   1.0000
   9.000   1.3701   0.02524   0.01627  -0.0686   0.1625   1.0000
   9.250   1.3916   0.02574   0.01699  -0.0676   0.1581   1.0000
   9.500   1.4133   0.02634   0.01765  -0.0668   0.1534   1.0000
   9.750   1.4353   0.02718   0.01842  -0.0662   0.1491   1.0000
  10.000   1.4559   0.02800   0.01939  -0.0652   0.1451   1.0000
  10.250   1.4757   0.02866   0.02018  -0.0641   0.1409   1.0000
  10.500   1.4955   0.02934   0.02087  -0.0631   0.1371   1.0000
  10.750   1.5164   0.03049   0.02199  -0.0624   0.1333   1.0000
  11.000   1.5326   0.03123   0.02297  -0.0608   0.1298   1.0000
  11.250   1.5493   0.03196   0.02380  -0.0594   0.1262   1.0000
  11.500   1.5666   0.03276   0.02458  -0.0581   0.1230   1.0000
  11.750   1.5840   0.03402   0.02590  -0.0570   0.1197   1.0000
  12.000   1.5945   0.03494   0.02706  -0.0546   0.1167   1.0000
  12.250   1.6059   0.03583   0.02806  -0.0525   0.1137   1.0000
  12.500   1.6177   0.03670   0.02895  -0.0505   0.1110   1.0000
  12.750   1.6349   0.03820   0.03041  -0.0496   0.1080   1.0000
  13.000   1.6346   0.03941   0.03189  -0.0460   0.1061   1.0000
  13.250   1.6373   0.04076   0.03344  -0.0431   0.1037   1.0000
  13.500   1.6426   0.04206   0.03485  -0.0408   0.1013   1.0000
  13.750   1.6511   0.04329   0.03612  -0.0391   0.0992   1.0000
  14.000   1.6670   0.04507   0.03783  -0.0384   0.0965   1.0000
  14.250   1.6621   0.04706   0.04011  -0.0357   0.0952   1.0000
  14.500   1.6579   0.04931   0.04261  -0.0335   0.0934   1.0000
  14.750   1.6558   0.05157   0.04507  -0.0318   0.0915   1.0000
  15.000   1.6567   0.05366   0.04728  -0.0305   0.0897   1.0000
  15.250   1.6619   0.05546   0.04911  -0.0296   0.0880   1.0000
  15.500   1.6721   0.05749   0.05109  -0.0287   0.0859   1.0000
  15.750   1.6603   0.06108   0.05496  -0.0277   0.0849   1.0000
  16.000   1.6459   0.06509   0.05924  -0.0272   0.0839   1.0000
  16.250   1.6307   0.06949   0.06391  -0.0273   0.0828   1.0000
  16.500   1.6143   0.07431   0.06897  -0.0279   0.0817   1.0000
  16.750   1.5977   0.07938   0.07424  -0.0289   0.0807   1.0000
  17.000   1.5827   0.08451   0.07955  -0.0303   0.0796   1.0000
  17.250   1.5721   0.08920   0.08438  -0.0318   0.0785   1.0000
  17.500   1.5750   0.09190   0.08709  -0.0323   0.0772   1.0000
  17.750   1.5769   0.09488   0.09006  -0.0323   0.0757   1.0000
  18.000   1.5404   0.10422   0.09968  -0.0370   0.0753   1.0000
  18.250   1.4901   0.11697   0.11275  -0.0445   0.0752   1.0000
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