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DFVLR R-4 AIRFOIL (dfvlrr4-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: DFVLR R-4 AIRFOIL (dfvlrr4-il)
Reynolds number: 50,000
Max Cl/Cd: 26.66 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dfvlrr4-il-50000.txt
Download as CSV file: xf-dfvlrr4-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5442   0.10327   0.09587  -0.0394   1.0000   0.2000
 -10.000  -0.6164   0.08604   0.07883  -0.0507   1.0000   0.1549
  -9.750  -0.6425   0.08071   0.07353  -0.0508   1.0000   0.1485
  -9.500  -0.6813   0.07611   0.06899  -0.0493   1.0000   0.1437
  -9.250  -0.7492   0.07037   0.06292  -0.0491   1.0000   0.1352
  -9.000  -0.7557   0.06627   0.05870  -0.0479   1.0000   0.1336
  -8.750  -0.7628   0.06218   0.05439  -0.0468   1.0000   0.1323
  -8.500  -0.7656   0.05811   0.05000  -0.0460   1.0000   0.1313
  -8.250  -0.7628   0.05414   0.04564  -0.0455   1.0000   0.1309
  -8.000  -0.7535   0.05039   0.04146  -0.0452   1.0000   0.1307
  -7.750  -0.7392   0.04685   0.03747  -0.0450   1.0000   0.1308
  -7.500  -0.7212   0.04369   0.03385  -0.0448   1.0000   0.1323
  -7.250  -0.7003   0.04110   0.03061  -0.0448   1.0000   0.1364
  -7.000  -0.6799   0.03847   0.02803  -0.0439   1.0000   0.1423
  -6.750  -0.6571   0.03638   0.02568  -0.0430   1.0000   0.1488
  -6.500  -0.6351   0.03443   0.02366  -0.0419   1.0000   0.1586
  -6.250  -0.6133   0.03280   0.02200  -0.0403   1.0000   0.1720
  -6.000  -0.5928   0.03138   0.02070  -0.0382   1.0000   0.1896
  -5.750  -0.5728   0.03005   0.01952  -0.0361   1.0000   0.2143
  -5.500  -0.5536   0.02846   0.01833  -0.0343   1.0000   0.2503
  -5.250  -0.5327   0.02566   0.01721  -0.0342   1.0000   0.3800
  -5.000  -0.5392   0.02865   0.02133  -0.0202   1.0000   0.5768
  -4.750  -0.5371   0.03238   0.02490  -0.0087   1.0000   0.6307
  -4.500  -0.5295   0.03495   0.02726  -0.0002   1.0000   0.6672
  -4.250  -0.5206   0.03692   0.02906   0.0077   1.0000   0.6968
  -4.000  -0.5096   0.03843   0.03040   0.0154   1.0000   0.7229
  -3.750  -0.4959   0.03907   0.03086   0.0208   1.0000   0.7494
  -3.500  -0.4825   0.03930   0.03093   0.0254   1.0000   0.7778
  -3.250  -0.4574   0.03984   0.03130   0.0308   1.0000   0.8187
  -3.000  -0.4114   0.03970   0.03087   0.0311   1.0000   0.8659
  -2.750  -0.3621   0.03868   0.02959   0.0271   1.0000   0.8873
  -2.500  -0.3405   0.03762   0.02837   0.0266   1.0000   0.9005
  -2.250  -0.3248   0.03661   0.02724   0.0271   1.0000   0.9123
  -2.000  -0.3064   0.03567   0.02618   0.0270   1.0000   0.9234
  -1.750  -0.2688   0.03483   0.02518   0.0234   1.0000   0.9339
  -1.500  -0.2362   0.03408   0.02430   0.0207   1.0000   0.9444
  -1.250  -0.2018   0.03342   0.02353   0.0176   1.0000   0.9551
  -1.000  -0.1658   0.03287   0.02287   0.0141   1.0000   0.9654
  -0.750  -0.1289   0.03242   0.02234   0.0104   1.0000   0.9751
  -0.500  -0.0868   0.03209   0.02193   0.0056   1.0000   0.9842
  -0.250  -0.0446   0.03185   0.02164   0.0008   1.0000   0.9928
   0.000  -0.0108   0.03167   0.02145  -0.0026   1.0000   1.0000
   0.250  -0.0082   0.03139   0.02118  -0.0001   1.0000   1.0000
   0.500  -0.0057   0.03113   0.02093   0.0024   1.0000   1.0000
   0.750  -0.0033   0.03088   0.02070   0.0049   1.0000   1.0000
   1.000  -0.0011   0.03065   0.02049   0.0074   1.0000   1.0000
   1.250   0.0011   0.03044   0.02031   0.0099   1.0000   1.0000
   1.500   0.0034   0.03024   0.02015   0.0123   1.0000   1.0000
   1.750   0.0060   0.03008   0.02003   0.0146   1.0000   1.0000
   2.000   0.0092   0.02996   0.01995   0.0167   1.0000   1.0000
   2.250   0.0153   0.02995   0.02000   0.0183   1.0000   1.0000
   2.500   0.0265   0.03014   0.02025   0.0188   1.0000   1.0000
   2.750   0.0422   0.03054   0.02071   0.0184   1.0000   1.0000
   3.000   0.0609   0.03112   0.02138   0.0173   1.0000   1.0000
   3.250   0.0815   0.03188   0.02223   0.0158   1.0000   1.0000
   3.500   0.1031   0.03281   0.02326   0.0139   1.0000   1.0000
   3.750   0.1755   0.03509   0.02571   0.0031   0.9750   1.0000
   4.000   0.2711   0.03655   0.02741  -0.0095   0.9243   1.0000
   4.250   0.3585   0.03625   0.02738  -0.0182   0.8750   1.0000
   4.500   0.4452   0.03449   0.02596  -0.0247   0.8319   1.0000
   4.750   0.5102   0.03200   0.02384  -0.0268   0.7896   1.0000
   5.000   0.5724   0.02807   0.02033  -0.0262   0.7347   1.0000
   5.250   0.6627   0.02486   0.01491  -0.0248   0.3923   1.0000
   5.500   0.6887   0.02648   0.01595  -0.0246   0.3327   1.0000
   5.750   0.7336   0.02803   0.01723  -0.0277   0.2975   1.0000
   6.000   0.7758   0.02956   0.01856  -0.0304   0.2751   1.0000
   6.250   0.8104   0.03105   0.02001  -0.0319   0.2589   1.0000
   6.500   0.8422   0.03263   0.02174  -0.0330   0.2479   1.0000
   6.750   0.8726   0.03450   0.02380  -0.0339   0.2399   1.0000
   7.000   0.9011   0.03632   0.02576  -0.0345   0.2313   1.0000
   7.250   0.9263   0.03840   0.02812  -0.0348   0.2240   1.0000
   7.500   0.9505   0.04053   0.03056  -0.0349   0.2176   1.0000
   7.750   0.9773   0.04300   0.03311  -0.0356   0.2109   1.0000
   8.000   0.9927   0.04566   0.03635  -0.0346   0.2069   1.0000
   8.250   1.0085   0.04866   0.03981  -0.0340   0.2036   1.0000
   8.500   1.0301   0.05149   0.04283  -0.0342   0.1982   1.0000
   8.750   1.0429   0.05503   0.04669  -0.0335   0.1941   1.0000
   9.000   1.0426   0.05896   0.05118  -0.0317   0.1924   1.0000
   9.250   1.0383   0.06326   0.05596  -0.0299   0.1911   1.0000
   9.500   1.0289   0.06801   0.06111  -0.0283   0.1908   1.0000
   9.750   1.0149   0.07327   0.06670  -0.0270   0.1920   1.0000
  10.000   1.0040   0.07889   0.07254  -0.0265   0.1941   1.0000
  10.250   0.8729   0.09444   0.08843  -0.0313   0.2167   1.0000
  10.500   0.9098   0.09680   0.09088  -0.0300   0.2127   1.0000
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