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RAE 5214 AIRFOIL (rae5214-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: RAE 5214 AIRFOIL (rae5214-il)
Reynolds number: 50,000
Max Cl/Cd: 29.22 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae5214-il-50000.txt
Download as CSV file: xf-rae5214-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 5214 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4405   0.10219   0.09483   0.0002   1.0000   0.3501
  -8.250  -0.4349   0.09924   0.09194   0.0008   1.0000   0.3658
  -8.000  -0.4296   0.09636   0.08911   0.0014   1.0000   0.3820
  -7.750  -0.4215   0.09338   0.08618   0.0023   1.0000   0.3996
  -7.500  -0.4124   0.09040   0.08324   0.0032   1.0000   0.4176
  -7.250  -0.4049   0.08750   0.08040   0.0041   1.0000   0.4346
  -7.000  -0.4035   0.08496   0.07794   0.0051   1.0000   0.4494
  -6.500  -0.5520   0.05664   0.04937  -0.0371   1.0000   0.1738
  -6.250  -0.5454   0.05047   0.04248  -0.0398   1.0000   0.1501
  -6.000  -0.5326   0.04594   0.03702  -0.0406   1.0000   0.1364
  -5.750  -0.5149   0.04222   0.03322  -0.0399   1.0000   0.1334
  -5.500  -0.4966   0.03912   0.02974  -0.0393   1.0000   0.1323
  -5.250  -0.4764   0.03642   0.02663  -0.0385   1.0000   0.1326
  -5.000  -0.4546   0.03392   0.02376  -0.0377   1.0000   0.1326
  -4.750  -0.4318   0.03176   0.02122  -0.0367   1.0000   0.1339
  -4.500  -0.4085   0.02992   0.01901  -0.0356   1.0000   0.1375
  -4.250  -0.3859   0.02797   0.01709  -0.0344   1.0000   0.1422
  -4.000  -0.3626   0.02651   0.01553  -0.0329   1.0000   0.1482
  -3.750  -0.3402   0.02511   0.01415  -0.0312   1.0000   0.1575
  -3.500  -0.3182   0.02401   0.01299  -0.0294   1.0000   0.1693
  -3.250  -0.2980   0.02267   0.01188  -0.0276   1.0000   0.1889
  -3.000  -0.2769   0.02103   0.01065  -0.0266   1.0000   0.2311
  -2.750  -0.2772   0.01939   0.01158  -0.0187   1.0000   0.6485
  -2.500  -0.2855   0.02034   0.01263  -0.0072   1.0000   0.7455
  -2.250  -0.2905   0.02055   0.01287   0.0026   1.0000   0.8004
  -2.000  -0.0834   0.02172   0.01314  -0.0145   1.0000   0.9806
  -1.750  -0.0263   0.02102   0.01219  -0.0217   1.0000   0.9966
  -1.500  -0.0138   0.02069   0.01180  -0.0210   1.0000   1.0000
  -1.250  -0.0160   0.02047   0.01157  -0.0177   1.0000   1.0000
  -1.000  -0.0197   0.02024   0.01134  -0.0142   1.0000   1.0000
  -0.750  -0.0249   0.02000   0.01110  -0.0106   1.0000   1.0000
  -0.500  -0.0314   0.01972   0.01083  -0.0068   1.0000   1.0000
  -0.250  -0.0383   0.01940   0.01051  -0.0030   1.0000   1.0000
   0.000  -0.0416   0.01910   0.01019   0.0001   1.0000   1.0000
   0.250  -0.0320   0.01898   0.01001   0.0012   1.0000   1.0000
   0.500  -0.0135   0.01904   0.00999   0.0008   1.0000   1.0000
   0.750   0.0090   0.01922   0.01010  -0.0001   1.0000   1.0000
   1.000   0.0332   0.01949   0.01032  -0.0012   1.0000   1.0000
   1.250   0.0577   0.01984   0.01062  -0.0024   1.0000   1.0000
   1.500   0.0821   0.02027   0.01101  -0.0035   1.0000   1.0000
   1.750   0.1059   0.02076   0.01148  -0.0045   1.0000   1.0000
   2.000   0.1290   0.02132   0.01204  -0.0054   1.0000   1.0000
   2.250   0.1513   0.02195   0.01269  -0.0063   1.0000   1.0000
   2.500   0.1738   0.02268   0.01346  -0.0073   0.9993   1.0000
   2.750   0.2951   0.02429   0.01540  -0.0244   0.9421   1.0000
   3.000   0.4104   0.02358   0.01518  -0.0363   0.8838   1.0000
   3.250   0.4998   0.02091   0.01303  -0.0398   0.8115   1.0000
   3.500   0.5405   0.01850   0.00987  -0.0315   0.5386   1.0000
   3.750   0.5569   0.02074   0.01044  -0.0284   0.3849   1.0000
   4.000   0.5847   0.02236   0.01152  -0.0283   0.3328   1.0000
   4.250   0.6154   0.02378   0.01270  -0.0286   0.2999   1.0000
   4.500   0.6465   0.02526   0.01400  -0.0289   0.2766   1.0000
   4.750   0.6764   0.02681   0.01548  -0.0291   0.2580   1.0000
   5.000   0.7053   0.02850   0.01710  -0.0291   0.2426   1.0000
   5.250   0.7327   0.03021   0.01888  -0.0290   0.2291   1.0000
   5.500   0.7583   0.03214   0.02109  -0.0286   0.2181   1.0000
   5.750   0.7838   0.03435   0.02330  -0.0284   0.2079   1.0000
   6.000   0.8065   0.03650   0.02587  -0.0276   0.1990   1.0000
   6.250   0.8295   0.03912   0.02852  -0.0272   0.1909   1.0000
   6.500   0.8470   0.04181   0.03179  -0.0261   0.1845   1.0000
   6.750   0.8673   0.04448   0.03460  -0.0255   0.1781   1.0000
   7.000   0.8841   0.04798   0.03833  -0.0248   0.1737   1.0000
   7.250   0.8931   0.05185   0.04278  -0.0236   0.1719   1.0000
   7.500   0.9002   0.05619   0.04757  -0.0228   0.1716   1.0000
   7.750   0.9038   0.06087   0.05261  -0.0222   0.1719   1.0000
   8.000   0.9066   0.06582   0.05782  -0.0219   0.1731   1.0000
   8.250   0.9216   0.07113   0.06315  -0.0220   0.1752   1.0000
   8.500   0.8501   0.08344   0.07618  -0.0271   0.2080   1.0000
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