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ARA-D 6% AIRFOIL (arad6-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: ARA-D 6% AIRFOIL (arad6-il)
Reynolds number: 50,000
Max Cl/Cd: 45.77 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-arad6-il-50000-n5.txt
Download as CSV file: xf-arad6-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ARA-D 6% 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3490   0.10786   0.10094  -0.0251   1.0000   0.0867
  -7.500  -0.3544   0.10634   0.09953  -0.0244   1.0000   0.0885
  -7.250  -0.3587   0.10522   0.09852  -0.0258   1.0000   0.0902
  -7.000  -0.3602   0.10413   0.09752  -0.0289   1.0000   0.0910
  -6.750  -0.3561   0.10250   0.09594  -0.0331   1.0000   0.0914
  -6.500  -0.3523   0.09743   0.09096  -0.0285   1.0000   0.0924
  -6.250  -0.3477   0.09392   0.08749  -0.0263   1.0000   0.0940
  -6.000  -0.3427   0.09105   0.08467  -0.0258   1.0000   0.0958
  -5.750  -0.3364   0.08833   0.08199  -0.0263   1.0000   0.0980
  -5.500  -0.3277   0.08562   0.07930  -0.0282   1.0000   0.1009
  -5.250  -0.3041   0.08337   0.07696  -0.0379   1.0000   0.1053
  -5.000  -0.2846   0.07993   0.07350  -0.0426   1.0000   0.1060
  -4.750  -0.2833   0.07620   0.06987  -0.0382   1.0000   0.1079
  -4.500  -0.2728   0.07332   0.06699  -0.0375   1.0000   0.1121
  -3.750  -0.1657   0.05800   0.05101  -0.0593   1.0000   0.0624
  -3.500  -0.1396   0.05458   0.04749  -0.0621   1.0000   0.0602
  -3.250  -0.1051   0.05075   0.04345  -0.0669   1.0000   0.0581
  -3.000  -0.0660   0.04675   0.03915  -0.0723   1.0000   0.0564
  -2.750  -0.0255   0.04296   0.03499  -0.0773   1.0000   0.0558
  -2.500   0.0128   0.04000   0.03161  -0.0813   1.0000   0.0585
  -2.250   0.0616   0.03650   0.02743  -0.0869   0.9985   0.0617
  -2.000   0.1114   0.03325   0.02336  -0.0919   0.9965   0.0635
  -1.750   0.1528   0.03153   0.02133  -0.0953   0.9932   0.0679
  -1.500   0.1949   0.03008   0.01932  -0.0984   0.9893   0.0786
  -1.250   0.2359   0.02914   0.01811  -0.1013   0.9856   0.0931
  -1.000   0.2730   0.02858   0.01738  -0.1034   0.9801   0.1141
  -0.750   0.3122   0.02805   0.01659  -0.1057   0.9754   0.1400
  -0.500   0.3498   0.02760   0.01593  -0.1077   0.9701   0.1661
  -0.250   0.3860   0.02729   0.01558  -0.1096   0.9639   0.1970
   0.000   0.4263   0.02699   0.01528  -0.1124   0.9592   0.2380
   0.250   0.4591   0.02670   0.01516  -0.1138   0.9511   0.2860
   0.500   0.4997   0.02591   0.01512  -0.1169   0.9466   0.4393
   0.750   0.5226   0.02509   0.01492  -0.1157   0.9354   1.0000
   1.000   0.5578   0.02540   0.01494  -0.1173   0.9273   1.0000
   1.250   0.5929   0.02568   0.01503  -0.1189   0.9188   1.0000
   1.500   0.6237   0.02599   0.01523  -0.1197   0.9087   1.0000
   1.750   0.6609   0.02619   0.01534  -0.1216   0.9008   1.0000
   2.000   0.6927   0.02644   0.01555  -0.1225   0.8904   1.0000
   2.250   0.7233   0.02669   0.01578  -0.1230   0.8793   1.0000
   2.500   0.7582   0.02671   0.01583  -0.1241   0.8673   1.0000
   2.750   0.7963   0.02627   0.01541  -0.1250   0.8508   1.0000
   3.000   0.8358   0.02552   0.01470  -0.1255   0.8324   1.0000
   3.250   0.8673   0.02506   0.01433  -0.1249   0.8122   1.0000
   3.500   0.8974   0.02478   0.01412  -0.1242   0.7935   1.0000
   3.750   0.9291   0.02442   0.01385  -0.1237   0.7748   1.0000
   4.000   0.9562   0.02426   0.01379  -0.1226   0.7527   1.0000
   4.250   0.9866   0.02393   0.01358  -0.1218   0.7295   1.0000
   4.500   1.0134   0.02377   0.01350  -0.1204   0.7007   1.0000
   4.750   1.0383   0.02372   0.01353  -0.1188   0.6657   1.0000
   5.000   1.0640   0.02368   0.01352  -0.1171   0.6233   1.0000
   5.250   1.0883   0.02379   0.01352  -0.1152   0.5688   1.0000
   5.500   1.1094   0.02424   0.01371  -0.1130   0.5003   1.0000
   5.750   1.1270   0.02511   0.01417  -0.1105   0.4272   1.0000
   6.000   1.1424   0.02631   0.01496  -0.1082   0.3673   1.0000
   6.250   1.1582   0.02760   0.01600  -0.1062   0.3240   1.0000
   6.500   1.1754   0.02889   0.01710  -0.1045   0.2923   1.0000
   6.750   1.1938   0.03015   0.01827  -0.1031   0.2665   1.0000
   7.000   1.2134   0.03138   0.01948  -0.1019   0.2447   1.0000
   7.250   1.2335   0.03260   0.02071  -0.1008   0.2249   1.0000
   7.500   1.2539   0.03385   0.02202  -0.0997   0.2078   1.0000
   7.750   1.2741   0.03513   0.02330  -0.0986   0.1920   1.0000
   8.000   1.2945   0.03643   0.02469  -0.0975   0.1774   1.0000
   8.250   1.3139   0.03776   0.02612  -0.0963   0.1637   1.0000
   8.500   1.3344   0.03919   0.02779  -0.0953   0.1514   1.0000
   8.750   1.3531   0.04069   0.02949  -0.0940   0.1396   1.0000
   9.000   1.3707   0.04227   0.03125  -0.0926   0.1289   1.0000
   9.250   1.3891   0.04396   0.03303  -0.0914   0.1206   1.0000
   9.500   1.4040   0.04569   0.03505  -0.0897   0.1115   1.0000
   9.750   1.4184   0.04767   0.03729  -0.0880   0.1036   1.0000
  10.000   1.4333   0.04968   0.03952  -0.0864   0.0974   1.0000
  10.250   1.4440   0.05214   0.04235  -0.0844   0.0910   1.0000
  10.500   1.4513   0.05412   0.04453  -0.0820   0.0851   1.0000
  10.750   1.4590   0.05688   0.04756  -0.0798   0.0807   1.0000
  11.000   1.4577   0.05991   0.05106  -0.0766   0.0761   1.0000
  11.250   1.4570   0.06185   0.05309  -0.0736   0.0720   1.0000
  11.500   1.4518   0.06486   0.05635  -0.0705   0.0689   1.0000
  11.750   1.4375   0.06886   0.06084  -0.0671   0.0666   1.0000
  12.000   1.4225   0.07284   0.06517  -0.0645   0.0643   1.0000
  12.250   1.4101   0.07648   0.06904  -0.0626   0.0620   1.0000
  12.500   1.4108   0.07851   0.07093  -0.0613   0.0585   1.0000
  12.750   1.3870   0.08414   0.07696  -0.0605   0.0579   1.0000
  13.000   1.3623   0.09041   0.08356  -0.0610   0.0576   1.0000
  13.250   1.3368   0.09741   0.09083  -0.0628   0.0577   1.0000
  13.500   1.3109   0.10522   0.09885  -0.0659   0.0580   1.0000
  13.750   1.2854   0.11386   0.10766  -0.0703   0.0584   1.0000
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