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DFVLR R-4 AIRFOIL (dfvlrr4-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: DFVLR R-4 AIRFOIL (dfvlrr4-il)
Reynolds number: 200,000
Max Cl/Cd: 46.3 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dfvlrr4-il-200000.txt
Download as CSV file: xf-dfvlrr4-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.4318   0.10852   0.10496  -0.0483   1.0000   0.0792
 -12.000  -0.5708   0.07027   0.06645  -0.0665   1.0000   0.0473
 -11.750  -0.5948   0.06452   0.06066  -0.0672   1.0000   0.0467
 -11.500  -0.6248   0.05910   0.05517  -0.0672   1.0000   0.0461
 -11.250  -0.6574   0.05443   0.05041  -0.0660   1.0000   0.0454
 -11.000  -0.7686   0.06273   0.05836  -0.0630   1.0000   0.0467
 -10.750  -0.7972   0.06095   0.05656  -0.0581   1.0000   0.0463
 -10.500  -0.8786   0.05361   0.04838  -0.0513   1.0000   0.0401
 -10.250  -0.8830   0.04995   0.04459  -0.0491   1.0000   0.0397
 -10.000  -0.8859   0.04662   0.04104  -0.0471   1.0000   0.0393
  -9.750  -0.8846   0.04335   0.03748  -0.0454   1.0000   0.0391
  -9.500  -0.8787   0.04023   0.03403  -0.0441   1.0000   0.0389
  -9.250  -0.8681   0.03760   0.03104  -0.0430   1.0000   0.0394
  -9.000  -0.8537   0.03551   0.02857  -0.0422   1.0000   0.0400
  -8.750  -0.8366   0.03362   0.02634  -0.0416   1.0000   0.0405
  -8.500  -0.8181   0.03088   0.02341  -0.0409   1.0000   0.0411
  -8.250  -0.7979   0.02921   0.02167  -0.0403   1.0000   0.0419
  -8.000  -0.7771   0.02799   0.02038  -0.0396   1.0000   0.0430
  -7.750  -0.7556   0.02690   0.01919  -0.0390   1.0000   0.0442
  -7.500  -0.7337   0.02593   0.01812  -0.0385   1.0000   0.0459
  -7.250  -0.7109   0.02519   0.01722  -0.0380   1.0000   0.0480
  -7.000  -0.6891   0.02391   0.01598  -0.0374   1.0000   0.0504
  -6.750  -0.6623   0.02312   0.01521  -0.0379   0.9993   0.0533
  -6.500  -0.6297   0.02241   0.01441  -0.0393   0.9977   0.0573
  -6.250  -0.5965   0.02145   0.01357  -0.0413   0.9961   0.0638
  -6.000  -0.5608   0.02064   0.01279  -0.0438   0.9948   0.0732
  -5.750  -0.5261   0.01983   0.01203  -0.0462   0.9932   0.0856
  -5.500  -0.4907   0.01909   0.01136  -0.0489   0.9917   0.1024
  -5.250  -0.4526   0.01826   0.01069  -0.0523   0.9904   0.1295
  -5.000  -0.3910   0.01544   0.00949  -0.0634   0.9927   0.4151
  -4.750  -0.3537   0.01517   0.00972  -0.0659   0.9915   0.5355
  -4.500  -0.3217   0.01542   0.01007  -0.0666   0.9890   0.5782
  -4.250  -0.2882   0.01577   0.01040  -0.0677   0.9868   0.6052
  -4.000  -0.2555   0.01627   0.01088  -0.0685   0.9849   0.6249
  -3.750  -0.2311   0.01671   0.01130  -0.0676   0.9810   0.6407
  -3.500  -0.2050   0.01733   0.01191  -0.0668   0.9777   0.6554
  -3.250  -0.1770   0.01807   0.01262  -0.0663   0.9749   0.6692
  -3.000  -0.1441   0.01877   0.01327  -0.0669   0.9728   0.6822
  -2.750  -0.1307   0.01936   0.01390  -0.0633   0.9679   0.6866
  -2.500  -0.1000   0.01973   0.01421  -0.0641   0.9648   0.6977
  -2.250  -0.0767   0.02039   0.01489  -0.0622   0.9616   0.7020
  -2.000  -0.0439   0.02082   0.01529  -0.0631   0.9596   0.7098
  -1.750  -0.0207   0.02100   0.01545  -0.0624   0.9548   0.7154
  -1.500   0.0052   0.02125   0.01570  -0.0618   0.9503   0.7192
  -1.250   0.0431   0.02135   0.01575  -0.0643   0.9474   0.7267
  -1.000   0.0788   0.02155   0.01595  -0.0657   0.9449   0.7312
  -0.750   0.0963   0.02180   0.01622  -0.0635   0.9381   0.7354
  -0.500   0.1369   0.02180   0.01618  -0.0669   0.9342   0.7443
  -0.250   0.1713   0.02183   0.01624  -0.0676   0.9305   0.7468
   0.000   0.1959   0.02192   0.01636  -0.0668   0.9237   0.7504
   0.250   0.2326   0.02181   0.01626  -0.0685   0.9178   0.7558
   0.500   0.2918   0.02118   0.01564  -0.0741   0.9135   0.7615
   0.750   0.3405   0.02003   0.01453  -0.0760   0.8995   0.7643
   1.000   0.3884   0.01899   0.01352  -0.0782   0.8879   0.7680
   1.250   0.4409   0.01804   0.01259  -0.0821   0.8825   0.7727
   1.500   0.4738   0.01758   0.01217  -0.0828   0.8720   0.7776
   1.750   0.5109   0.01686   0.01150  -0.0833   0.8650   0.7806
   2.000   0.5368   0.01651   0.01121  -0.0821   0.8523   0.7848
   2.250   0.5706   0.01607   0.01081  -0.0830   0.8387   0.7899
   2.500   0.6011   0.01560   0.01037  -0.0829   0.8211   0.7938
   2.750   0.6247   0.01524   0.01005  -0.0811   0.7991   0.7973
   3.000   0.6508   0.01494   0.00974  -0.0799   0.7647   0.8020
   3.250   0.6838   0.01477   0.00925  -0.0804   0.6661   0.8076
   3.500   0.6866   0.01579   0.00920  -0.0746   0.4792   0.8107
   3.750   0.6893   0.01719   0.00974  -0.0700   0.3214   0.8148
   4.000   0.7035   0.01841   0.01032  -0.0683   0.2178   0.8194
   4.250   0.7268   0.01922   0.01083  -0.0682   0.1824   0.8231
   4.500   0.7447   0.01967   0.01120  -0.0663   0.1668   0.8258
   4.750   0.7655   0.02013   0.01163  -0.0651   0.1560   0.8292
   5.000   0.7882   0.02082   0.01221  -0.0645   0.1474   0.8332
   5.250   0.8181   0.02133   0.01275  -0.0654   0.1405   0.8372
   5.500   0.8389   0.02178   0.01317  -0.0642   0.1349   0.8399
   5.750   0.8618   0.02236   0.01376  -0.0634   0.1296   0.8427
   6.000   0.8869   0.02277   0.01421  -0.0632   0.1245   0.8460
   6.250   0.9144   0.02338   0.01478  -0.0636   0.1199   0.8494
   6.500   0.9460   0.02436   0.01572  -0.0649   0.1159   0.8521
   6.750   0.9693   0.02474   0.01623  -0.0641   0.1127   0.8544
   7.000   0.9933   0.02524   0.01680  -0.0636   0.1093   0.8572
   7.250   1.0193   0.02589   0.01744  -0.0636   0.1061   0.8602
   7.500   1.0510   0.02738   0.01891  -0.0649   0.1024   0.8630
   7.750   1.0789   0.02798   0.01970  -0.0653   0.0998   0.8656
   8.000   1.1043   0.02870   0.02055  -0.0651   0.0967   0.8681
   8.250   1.1273   0.02941   0.02137  -0.0644   0.0937   0.8708
   8.500   1.1531   0.03044   0.02239  -0.0645   0.0906   0.8735
   8.750   1.1791   0.03210   0.02422  -0.0647   0.0873   0.8760
   9.000   1.2015   0.03279   0.02512  -0.0641   0.0839   0.8788
   9.250   1.2249   0.03351   0.02595  -0.0639   0.0805   0.8816
   9.500   1.2461   0.03436   0.02678  -0.0633   0.0777   0.8840
   9.750   1.2663   0.03632   0.02895  -0.0626   0.0750   0.8863
  10.000   1.2829   0.03740   0.03034  -0.0610   0.0727   0.8892
  10.250   1.3014   0.03841   0.03153  -0.0600   0.0700   0.8921
  10.500   1.3208   0.03910   0.03227  -0.0593   0.0676   0.8946
  10.750   1.3430   0.04122   0.03434  -0.0596   0.0650   0.8966
  11.000   1.3485   0.04217   0.03571  -0.0563   0.0632   0.8990
  11.250   1.3574   0.04325   0.03704  -0.0539   0.0607   0.9016
  11.500   1.3700   0.04370   0.03755  -0.0522   0.0585   0.9047
  11.750   1.3879   0.04414   0.03787  -0.0515   0.0565   0.9077
  12.000   1.3867   0.04631   0.04034  -0.0482   0.0547   0.9102
  12.250   1.3799   0.04804   0.04244  -0.0440   0.0530   0.9128
  12.500   1.3793   0.04962   0.04423  -0.0410   0.0513   0.9156
  12.750   1.3837   0.05064   0.04534  -0.0390   0.0498   0.9185
  13.000   1.3974   0.05112   0.04573  -0.0380   0.0483   0.9215
  13.250   1.3956   0.05382   0.04857  -0.0361   0.0470   0.9241
  13.500   1.3760   0.05720   0.05236  -0.0327   0.0461   0.9271
  13.750   1.3555   0.06118   0.05672  -0.0303   0.0453   0.9302
  14.000   1.3339   0.06573   0.06159  -0.0288   0.0445   0.9332
  14.250   1.3124   0.07063   0.06677  -0.0284   0.0439   0.9360
  14.500   1.2839   0.07697   0.07341  -0.0292   0.0436   0.9384
  14.750   1.2302   0.08796   0.08479  -0.0333   0.0442   0.9397
  15.000   1.1624   0.10443   0.10163  -0.0434   0.0457   0.9397
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