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DFVLR R-4 AIRFOIL (dfvlrr4-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: DFVLR R-4 AIRFOIL (dfvlrr4-il)
Reynolds number: 50,000
Max Cl/Cd: 25.37 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dfvlrr4-il-50000-n5.txt
Download as CSV file: xf-dfvlrr4-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DFVLR R-4 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.5813   0.10251   0.09453  -0.0527   1.0000   0.0569
 -12.000  -0.6009   0.09484   0.08686  -0.0567   1.0000   0.0564
 -11.750  -0.6258   0.08754   0.07954  -0.0605   1.0000   0.0559
 -11.500  -0.6522   0.08132   0.07327  -0.0631   1.0000   0.0555
 -11.250  -0.6787   0.07620   0.06807  -0.0642   1.0000   0.0552
 -11.000  -0.7046   0.07206   0.06384  -0.0638   1.0000   0.0550
 -10.750  -0.7302   0.06874   0.06044  -0.0620   1.0000   0.0548
 -10.500  -0.7548   0.06592   0.05753  -0.0592   1.0000   0.0547
 -10.250  -0.7727   0.06282   0.05425  -0.0572   1.0000   0.0548
 -10.000  -0.7857   0.05979   0.05099  -0.0550   1.0000   0.0550
  -9.750  -0.7939   0.05680   0.04771  -0.0529   1.0000   0.0557
  -9.500  -0.7980   0.05382   0.04435  -0.0510   1.0000   0.0567
  -9.250  -0.7971   0.05095   0.04106  -0.0493   1.0000   0.0579
  -9.000  -0.7864   0.04896   0.03905  -0.0480   1.0000   0.0596
  -8.750  -0.7753   0.04697   0.03690  -0.0466   1.0000   0.0614
  -8.500  -0.7624   0.04482   0.03451  -0.0452   1.0000   0.0632
  -8.250  -0.7473   0.04272   0.03209  -0.0438   1.0000   0.0651
  -8.000  -0.7308   0.04084   0.02979  -0.0424   1.0000   0.0681
  -7.750  -0.7139   0.03944   0.02849  -0.0411   1.0000   0.0714
  -7.500  -0.6959   0.03813   0.02705  -0.0396   1.0000   0.0757
  -7.250  -0.6762   0.03689   0.02556  -0.0376   1.0000   0.0801
  -7.000  -0.6588   0.03582   0.02461  -0.0359   1.0000   0.0855
  -6.750  -0.6400   0.03493   0.02353  -0.0340   1.0000   0.0930
  -6.500  -0.6237   0.03393   0.02264  -0.0324   1.0000   0.1012
  -6.250  -0.6069   0.03295   0.02166  -0.0309   1.0000   0.1111
  -6.000  -0.5899   0.03192   0.02062  -0.0297   1.0000   0.1238
  -5.750  -0.5724   0.03076   0.01952  -0.0289   1.0000   0.1394
  -5.500  -0.5534   0.02936   0.01831  -0.0289   1.0000   0.1623
  -5.250  -0.5313   0.02753   0.01692  -0.0302   1.0000   0.2091
  -5.000  -0.5109   0.02556   0.01650  -0.0310   1.0000   0.4005
  -4.750  -0.4977   0.02614   0.01751  -0.0265   1.0000   0.5062
  -4.500  -0.4815   0.02694   0.01830  -0.0229   1.0000   0.5591
  -4.250  -0.4645   0.02777   0.01902  -0.0198   1.0000   0.5940
  -4.000  -0.4466   0.02859   0.01968  -0.0170   1.0000   0.6227
  -3.500  -0.4211   0.03085   0.02176  -0.0078   1.0000   0.6731
  -3.250  -0.4052   0.03163   0.02241  -0.0046   1.0000   0.6979
  -3.000  -0.3892   0.03202   0.02268  -0.0018   1.0000   0.7136
  -2.750  -0.3715   0.03205   0.02259   0.0003   1.0000   0.7228
  -2.500  -0.3484   0.03185   0.02223   0.0003   1.0000   0.7319
  -2.250  -0.3258   0.03170   0.02193   0.0005   1.0000   0.7408
  -2.000  -0.3042   0.03157   0.02169   0.0010   1.0000   0.7491
  -1.750  -0.2796   0.03146   0.02145   0.0005   1.0000   0.7588
  -1.500  -0.2568   0.03138   0.02128   0.0010   0.9987   0.7659
  -1.250  -0.2227   0.03142   0.02119  -0.0014   0.9952   0.7746
  -1.000  -0.1937   0.03141   0.02110  -0.0022   0.9909   0.7813
  -0.750  -0.1602   0.03149   0.02108  -0.0043   0.9865   0.7895
  -0.500  -0.1300   0.03152   0.02105  -0.0055   0.9818   0.7965
  -0.250  -0.0983   0.03159   0.02106  -0.0072   0.9768   0.8038
   0.000  -0.0641   0.03172   0.02114  -0.0093   0.9721   0.8106
   0.250  -0.0353   0.03173   0.02114  -0.0103   0.9655   0.8171
   0.500   0.0019   0.03192   0.02130  -0.0131   0.9601   0.8238
   0.750   0.0288   0.03193   0.02133  -0.0136   0.9531   0.8300
   1.000   0.0656   0.03214   0.02154  -0.0163   0.9467   0.8371
   1.250   0.0940   0.03216   0.02161  -0.0169   0.9388   0.8430
   1.500   0.1298   0.03231   0.02180  -0.0192   0.9311   0.8497
   1.750   0.1597   0.03236   0.02192  -0.0203   0.9218   0.8556
   2.000   0.1981   0.03244   0.02207  -0.0227   0.9137   0.8615
   2.250   0.2297   0.03249   0.02220  -0.0241   0.9019   0.8672
   2.500   0.2606   0.03241   0.02224  -0.0249   0.8905   0.8723
   2.750   0.3002   0.03229   0.02224  -0.0272   0.8790   0.8777
   3.000   0.3365   0.03189   0.02198  -0.0284   0.8609   0.8828
   3.250   0.3766   0.03091   0.02114  -0.0292   0.8371   0.8876
   3.500   0.4142   0.02973   0.02009  -0.0292   0.8084   0.8923
   3.750   0.4494   0.02859   0.01912  -0.0289   0.7798   0.8967
   4.000   0.4766   0.02758   0.01825  -0.0273   0.7494   0.9012
   4.250   0.4976   0.02702   0.01785  -0.0254   0.7120   0.9064
   4.500   0.5206   0.02647   0.01745  -0.0237   0.6620   0.9113
   4.750   0.5744   0.02462   0.01530  -0.0243   0.5537   0.9145
   5.000   0.6075   0.02497   0.01464  -0.0237   0.4002   0.9183
   5.250   0.6194   0.02616   0.01520  -0.0216   0.3134   0.9235
   5.500   0.6331   0.02719   0.01581  -0.0198   0.2626   0.9283
   5.750   0.6519   0.02810   0.01650  -0.0190   0.2313   0.9334
   6.000   0.6745   0.02898   0.01724  -0.0188   0.2104   0.9384
   6.250   0.6993   0.02977   0.01795  -0.0187   0.1960   0.9434
   6.500   0.7294   0.03055   0.01877  -0.0195   0.1835   0.9483
   6.750   0.7618   0.03136   0.01964  -0.0206   0.1727   0.9533
   7.000   0.7959   0.03225   0.02045  -0.0220   0.1634   0.9585
   7.250   0.8327   0.03320   0.02162  -0.0237   0.1558   0.9638
   7.500   0.8696   0.03434   0.02281  -0.0256   0.1499   0.9693
   7.750   0.9051   0.03567   0.02430  -0.0273   0.1441   0.9760
   8.250   0.9685   0.03842   0.02724  -0.0301   0.1326   1.0000
   8.500   0.9950   0.04014   0.02936  -0.0307   0.1274   1.0000
   8.750   1.0214   0.04190   0.03140  -0.0314   0.1226   1.0000
   9.000   1.0491   0.04376   0.03336  -0.0324   0.1188   1.0000
   9.250   1.0710   0.04599   0.03592  -0.0326   0.1149   1.0000
   9.500   1.0872   0.04820   0.03859  -0.0321   0.1101   1.0000
   9.750   1.1062   0.05019   0.04079  -0.0320   0.1060   1.0000
  10.000   1.1300   0.05226   0.04282  -0.0328   0.1026   1.0000
  10.250   1.1318   0.05554   0.04676  -0.0307   0.1000   1.0000
  10.500   1.1320   0.05904   0.05081  -0.0289   0.0980   1.0000
  10.750   1.1284   0.06264   0.05484  -0.0269   0.0962   1.0000
  11.000   1.1205   0.06611   0.05866  -0.0248   0.0946   1.0000
  11.250   1.1118   0.06955   0.06237  -0.0229   0.0930   1.0000
  11.500   1.1115   0.07255   0.06552  -0.0221   0.0911   1.0000
  11.750   1.1254   0.07493   0.06786  -0.0222   0.0887   1.0000
  12.000   1.0941   0.08013   0.07343  -0.0207   0.0884   1.0000
  12.250   1.0601   0.08635   0.07994  -0.0211   0.0883   1.0000
  12.500   1.0231   0.09399   0.08782  -0.0235   0.0883   1.0000
  12.750   0.9842   0.10356   0.09756  -0.0286   0.0886   1.0000
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