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DFVLR R-4 AIRFOIL (dfvlrr4-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: DFVLR R-4 AIRFOIL (dfvlrr4-il)
Reynolds number: 100,000
Max Cl/Cd: 33.83 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dfvlrr4-il-100000-n5.txt
Download as CSV file: xf-dfvlrr4-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.6430   0.09035   0.08454  -0.0581   1.0000   0.0325
 -12.750  -0.6761   0.08100   0.07506  -0.0638   1.0000   0.0321
 -12.500  -0.7058   0.07383   0.06774  -0.0675   1.0000   0.0319
 -12.250  -0.7323   0.06818   0.06192  -0.0694   1.0000   0.0318
 -12.000  -0.7567   0.06360   0.05718  -0.0698   1.0000   0.0317
 -11.750  -0.7793   0.05986   0.05327  -0.0688   1.0000   0.0317
 -11.500  -0.8008   0.05679   0.05004  -0.0667   1.0000   0.0317
 -11.250  -0.8228   0.05436   0.04747  -0.0633   1.0000   0.0318
 -11.000  -0.8436   0.05223   0.04520  -0.0594   1.0000   0.0318
 -10.750  -0.8571   0.04972   0.04246  -0.0565   1.0000   0.0320
 -10.500  -0.8653   0.04721   0.03968  -0.0538   1.0000   0.0322
 -10.250  -0.8681   0.04476   0.03691  -0.0514   1.0000   0.0326
 -10.000  -0.8661   0.04241   0.03421  -0.0492   1.0000   0.0330
  -9.750  -0.8588   0.04047   0.03209  -0.0475   1.0000   0.0337
  -9.500  -0.8482   0.03912   0.03070  -0.0461   1.0000   0.0346
  -9.250  -0.8364   0.03783   0.02929  -0.0447   1.0000   0.0357
  -9.000  -0.8230   0.03641   0.02770  -0.0434   1.0000   0.0370
  -8.750  -0.8079   0.03490   0.02599  -0.0421   1.0000   0.0382
  -8.500  -0.7915   0.03343   0.02430  -0.0408   1.0000   0.0394
  -8.250  -0.7741   0.03210   0.02278  -0.0394   1.0000   0.0405
  -8.000  -0.7522   0.03089   0.02161  -0.0394   0.9990   0.0421
  -7.750  -0.7247   0.02988   0.02055  -0.0403   0.9968   0.0447
  -7.500  -0.6962   0.02888   0.01937  -0.0411   0.9947   0.0481
  -7.250  -0.6697   0.02779   0.01833  -0.0418   0.9924   0.0510
  -7.000  -0.6420   0.02685   0.01736  -0.0427   0.9899   0.0549
  -6.750  -0.6136   0.02596   0.01645  -0.0439   0.9876   0.0603
  -6.500  -0.5835   0.02524   0.01566  -0.0452   0.9857   0.0677
  -6.250  -0.5543   0.02441   0.01486  -0.0467   0.9837   0.0760
  -6.000  -0.5257   0.02364   0.01411  -0.0480   0.9810   0.0876
  -5.750  -0.4948   0.02289   0.01341  -0.0497   0.9786   0.1044
  -5.500  -0.4620   0.02207   0.01270  -0.0520   0.9765   0.1275
  -5.250  -0.4275   0.02107   0.01197  -0.0548   0.9749   0.1727
  -5.000  -0.3888   0.01924   0.01125  -0.0598   0.9745   0.3597
  -4.750  -0.3561   0.01891   0.01143  -0.0612   0.9731   0.4788
  -4.500  -0.3310   0.01910   0.01180  -0.0603   0.9701   0.5321
  -4.250  -0.3049   0.01942   0.01215  -0.0597   0.9665   0.5680
  -4.000  -0.2780   0.01992   0.01265  -0.0589   0.9632   0.5965
  -3.750  -0.2485   0.02047   0.01313  -0.0588   0.9607   0.6220
  -3.500  -0.2219   0.02109   0.01370  -0.0579   0.9581   0.6393
  -3.250  -0.2000   0.02159   0.01414  -0.0563   0.9536   0.6537
  -3.000  -0.1716   0.02197   0.01443  -0.0563   0.9503   0.6670
  -2.750  -0.1458   0.02237   0.01479  -0.0554   0.9472   0.6725
  -2.500  -0.1093   0.02236   0.01465  -0.0577   0.9453   0.6811
  -2.250  -0.0839   0.02256   0.01481  -0.0573   0.9419   0.6857
  -2.000  -0.0590   0.02272   0.01492  -0.0569   0.9377   0.6919
  -1.750  -0.0270   0.02278   0.01491  -0.0582   0.9345   0.6994
  -1.500   0.0019   0.02296   0.01507  -0.0584   0.9317   0.7039
  -1.250   0.0388   0.02298   0.01502  -0.0608   0.9296   0.7112
  -1.000   0.0630   0.02313   0.01517  -0.0603   0.9252   0.7156
  -0.750   0.0882   0.02328   0.01532  -0.0598   0.9203   0.7201
  -0.500   0.1243   0.02329   0.01530  -0.0621   0.9170   0.7272
   0.000   0.1800   0.02349   0.01555  -0.0621   0.9074   0.7355
   0.250   0.2138   0.02349   0.01556  -0.0637   0.9026   0.7410
   0.500   0.2521   0.02343   0.01551  -0.0659   0.8990   0.7458
   0.750   0.2764   0.02348   0.01563  -0.0651   0.8916   0.7494
   1.000   0.3107   0.02335   0.01554  -0.0663   0.8850   0.7537
   1.250   0.3583   0.02296   0.01520  -0.0700   0.8801   0.7589
   1.500   0.3976   0.02221   0.01451  -0.0709   0.8659   0.7625
   1.750   0.4339   0.02120   0.01355  -0.0706   0.8453   0.7661
   2.000   0.4667   0.02043   0.01282  -0.0702   0.8232   0.7706
   2.250   0.5028   0.01991   0.01233  -0.0714   0.8044   0.7759
   2.500   0.5294   0.01958   0.01208  -0.0703   0.7859   0.7791
   2.750   0.5507   0.01944   0.01204  -0.0686   0.7619   0.7827
   3.000   0.5789   0.01915   0.01179  -0.0681   0.7275   0.7865
   3.250   0.6258   0.01850   0.01076  -0.0703   0.6160   0.7901
   3.500   0.6489   0.01933   0.01054  -0.0687   0.4455   0.7936
   3.750   0.6614   0.02033   0.01093  -0.0660   0.3345   0.7970
   4.000   0.6794   0.02119   0.01134  -0.0645   0.2570   0.8007
   4.250   0.7022   0.02191   0.01180  -0.0642   0.2109   0.8043
   4.500   0.7268   0.02255   0.01227  -0.0641   0.1836   0.8079
   4.750   0.7469   0.02306   0.01270  -0.0629   0.1670   0.8106
   5.000   0.7688   0.02356   0.01320  -0.0620   0.1546   0.8136
   5.250   0.7914   0.02414   0.01372  -0.0614   0.1455   0.8168
   5.500   0.8164   0.02470   0.01431  -0.0613   0.1379   0.8202
   6.000   0.8619   0.02592   0.01558  -0.0601   0.1275   0.8259
   6.250   0.8848   0.02652   0.01623  -0.0594   0.1230   0.8287
   6.500   0.9085   0.02724   0.01692  -0.0591   0.1189   0.8318
   6.750   0.9346   0.02801   0.01774  -0.0592   0.1147   0.8350
   7.000   0.9617   0.02873   0.01855  -0.0596   0.1101   0.8378
   7.250   0.9843   0.02939   0.01926  -0.0589   0.1064   0.8403
   7.500   1.0083   0.03029   0.02012  -0.0586   0.1032   0.8430
   7.750   1.0341   0.03114   0.02114  -0.0586   0.1001   0.8459
   8.000   1.0597   0.03197   0.02214  -0.0586   0.0962   0.8488
   8.250   1.0847   0.03280   0.02303  -0.0587   0.0924   0.8517
   8.500   1.1070   0.03373   0.02395  -0.0583   0.0893   0.8542
   8.750   1.1298   0.03476   0.02521  -0.0577   0.0865   0.8568
   9.000   1.1529   0.03588   0.02658  -0.0573   0.0837   0.8594
   9.250   1.1757   0.03704   0.02792  -0.0570   0.0809   0.8619
   9.500   1.1983   0.03821   0.02920  -0.0568   0.0786   0.8647
   9.750   1.2215   0.03958   0.03056  -0.0568   0.0764   0.8674
  10.000   1.2367   0.04104   0.03240  -0.0551   0.0738   0.8700
  10.250   1.2505   0.04242   0.03412  -0.0535   0.0708   0.8728
  10.500   1.2649   0.04359   0.03547  -0.0521   0.0683   0.8756
  10.750   1.2808   0.04453   0.03645  -0.0511   0.0662   0.8783
  11.000   1.2933   0.04612   0.03823  -0.0497   0.0641   0.8809
  11.250   1.2954   0.04808   0.04062  -0.0466   0.0619   0.8836
  11.500   1.2977   0.04976   0.04259  -0.0438   0.0600   0.8868
  11.750   1.3025   0.05124   0.04425  -0.0415   0.0583   0.8902
  12.000   1.3095   0.05261   0.04572  -0.0398   0.0570   0.8936
  12.250   1.3195   0.05392   0.04701  -0.0385   0.0557   0.8967
  12.500   1.3046   0.05730   0.05089  -0.0351   0.0544   0.8995
  12.750   1.2884   0.06097   0.05500  -0.0323   0.0531   0.9025
  13.000   1.2716   0.06487   0.05926  -0.0304   0.0520   0.9056
  13.250   1.2544   0.06904   0.06372  -0.0292   0.0511   0.9087
  13.500   1.2359   0.07350   0.06845  -0.0287   0.0503   0.9119
  13.750   1.2128   0.07892   0.07414  -0.0293   0.0498   0.9150
  14.000   1.1701   0.08810   0.08368  -0.0325   0.0499   0.9172
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