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RAE(NPL) 5212 AIRFOIL (rae5212-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: RAE(NPL) 5212 AIRFOIL (rae5212-il)
Reynolds number: 200,000
Max Cl/Cd: 57.8 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae5212-il-200000.txt
Download as CSV file: xf-rae5212-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE(NPL) 5212 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4945   0.08860   0.08489  -0.0456   1.0000   0.0664
  -9.750  -0.5438   0.07855   0.07484  -0.0551   1.0000   0.0674
  -9.500  -0.5714   0.07449   0.07077  -0.0558   1.0000   0.0674
  -9.250  -0.6015   0.07181   0.06808  -0.0537   1.0000   0.0673
  -9.000  -0.6381   0.06954   0.06569  -0.0507   1.0000   0.0677
  -8.750  -0.6688   0.06800   0.06390  -0.0471   1.0000   0.0681
  -8.500  -0.6849   0.06636   0.06203  -0.0439   1.0000   0.0683
  -8.250  -0.6781   0.05860   0.05453  -0.0439   1.0000   0.0701
  -8.000  -0.6742   0.05622   0.05219  -0.0419   1.0000   0.0712
  -7.750  -0.6730   0.05404   0.04999  -0.0397   1.0000   0.0726
  -7.500  -0.6735   0.05176   0.04759  -0.0376   1.0000   0.0747
  -7.000  -0.6847   0.03674   0.03087  -0.0322   1.0000   0.0498
  -6.750  -0.6621   0.03267   0.02636  -0.0320   0.9984   0.0448
  -6.500  -0.6321   0.02886   0.02197  -0.0332   0.9954   0.0431
  -6.250  -0.5998   0.02665   0.01943  -0.0344   0.9924   0.0434
  -6.000  -0.5671   0.02532   0.01787  -0.0358   0.9886   0.0455
  -5.750  -0.5327   0.02396   0.01624  -0.0371   0.9855   0.0468
  -5.500  -0.4986   0.02296   0.01499  -0.0384   0.9824   0.0480
  -5.250  -0.4700   0.02121   0.01328  -0.0389   0.9786   0.0501
  -5.000  -0.4358   0.02050   0.01259  -0.0405   0.9748   0.0538
  -4.750  -0.3985   0.01990   0.01189  -0.0424   0.9722   0.0571
  -4.500  -0.3738   0.01877   0.01086  -0.0423   0.9666   0.0611
  -4.250  -0.3400   0.01822   0.01030  -0.0437   0.9625   0.0671
  -4.000  -0.3045   0.01735   0.00951  -0.0457   0.9597   0.0752
  -3.750  -0.2794   0.01671   0.00891  -0.0456   0.9533   0.0865
  -3.500  -0.2472   0.01588   0.00825  -0.0469   0.9490   0.1188
  -3.250  -0.2223   0.01365   0.00796  -0.0480   0.9459   0.5233
  -3.000  -0.1983   0.01387   0.00822  -0.0469   0.9389   0.5868
  -2.750  -0.1652   0.01414   0.00846  -0.0475   0.9343   0.6191
  -2.500  -0.1282   0.01440   0.00874  -0.0488   0.9315   0.6421
  -2.250  -0.1048   0.01465   0.00898  -0.0476   0.9245   0.6595
  -2.000  -0.0730   0.01488   0.00922  -0.0478   0.9200   0.6794
  -1.750  -0.0385   0.01515   0.00955  -0.0482   0.9171   0.7028
  -1.500  -0.0141   0.01531   0.00972  -0.0472   0.9108   0.7176
  -1.250   0.0170   0.01527   0.00969  -0.0475   0.9060   0.7251
  -1.000   0.0559   0.01513   0.00947  -0.0498   0.9031   0.7311
  -0.750   0.0970   0.01492   0.00925  -0.0523   0.9012   0.7354
  -0.500   0.1190   0.01493   0.00925  -0.0512   0.8932   0.7400
  -0.250   0.1586   0.01471   0.00900  -0.0535   0.8895   0.7452
   0.000   0.2028   0.01439   0.00865  -0.0565   0.8868   0.7497
   0.250   0.2462   0.01405   0.00833  -0.0592   0.8846   0.7537
   0.500   0.2684   0.01399   0.00829  -0.0579   0.8745   0.7584
   0.750   0.3164   0.01342   0.00770  -0.0612   0.8697   0.7633
   1.000   0.3473   0.01304   0.00733  -0.0611   0.8579   0.7674
   1.250   0.3834   0.01254   0.00683  -0.0618   0.8454   0.7715
   1.500   0.4166   0.01206   0.00632  -0.0618   0.8279   0.7764
   1.750   0.4467   0.01175   0.00596  -0.0616   0.8102   0.7813
   2.000   0.4742   0.01156   0.00580  -0.0610   0.7955   0.7857
   2.250   0.5017   0.01143   0.00569  -0.0605   0.7811   0.7909
   2.500   0.5289   0.01134   0.00557  -0.0600   0.7648   0.7966
   2.750   0.5543   0.01121   0.00548  -0.0591   0.7459   0.8015
   3.000   0.5805   0.01112   0.00537  -0.0582   0.7231   0.8073
   3.250   0.6045   0.01108   0.00529  -0.0571   0.6937   0.8136
   3.500   0.6267   0.01106   0.00521  -0.0555   0.6545   0.8196
   3.750   0.6468   0.01119   0.00514  -0.0535   0.5904   0.8268
   4.000   0.6590   0.01171   0.00515  -0.0501   0.4827   0.8337
   4.250   0.6646   0.01272   0.00548  -0.0460   0.3533   0.8428
   4.500   0.6707   0.01390   0.00601  -0.0424   0.2308   0.8524
   4.750   0.6833   0.01482   0.00654  -0.0398   0.1714   0.8637
   5.000   0.7008   0.01540   0.00702  -0.0380   0.1500   0.8771
   5.250   0.7203   0.01590   0.00751  -0.0365   0.1388   0.8953
   5.500   0.7451   0.01648   0.00808  -0.0362   0.1307   0.9271
   5.750   0.7819   0.01710   0.00875  -0.0386   0.1238   1.0000
   6.000   0.8070   0.01772   0.00929  -0.0386   0.1186   1.0000
   6.250   0.8312   0.01870   0.01014  -0.0385   0.1143   1.0000
   6.500   0.8569   0.01927   0.01076  -0.0383   0.1114   1.0000
   6.750   0.8823   0.01993   0.01142  -0.0381   0.1081   1.0000
   7.000   0.9073   0.02063   0.01208  -0.0379   0.1049   1.0000
   7.250   0.9346   0.02179   0.01314  -0.0382   0.1015   1.0000
   7.500   0.9613   0.02273   0.01414  -0.0382   0.0995   1.0000
   7.750   0.9870   0.02352   0.01503  -0.0380   0.0975   1.0000
   8.000   1.0128   0.02442   0.01602  -0.0378   0.0953   1.0000
   8.250   1.0378   0.02532   0.01697  -0.0375   0.0930   1.0000
   8.500   1.0628   0.02628   0.01793  -0.0373   0.0908   1.0000
   8.750   1.0908   0.02793   0.01956  -0.0378   0.0885   1.0000
   9.000   1.1158   0.02973   0.02154  -0.0377   0.0871   1.0000
   9.250   1.1368   0.03084   0.02287  -0.0367   0.0859   1.0000
   9.500   1.1568   0.03208   0.02433  -0.0356   0.0843   1.0000
   9.750   1.1762   0.03340   0.02584  -0.0345   0.0825   1.0000
  10.000   1.1953   0.03487   0.02749  -0.0335   0.0810   1.0000
  10.250   1.2148   0.03620   0.02892  -0.0326   0.0793   1.0000
  10.500   1.2332   0.03756   0.03033  -0.0317   0.0776   1.0000
  10.750   1.2488   0.04145   0.03434  -0.0313   0.0755   1.0000
  11.000   1.2545   0.04231   0.03556  -0.0281   0.0743   1.0000
  11.250   1.2586   0.04390   0.03749  -0.0252   0.0727   1.0000
  11.500   1.2616   0.04584   0.03971  -0.0223   0.0710   1.0000
  11.750   1.2647   0.04772   0.04181  -0.0197   0.0695   1.0000
  12.000   1.2740   0.04890   0.04306  -0.0178   0.0678   1.0000
  12.250   1.2886   0.04994   0.04408  -0.0167   0.0662   1.0000
  12.500   1.2955   0.05271   0.04688  -0.0154   0.0647   1.0000
  12.750   1.2744   0.05650   0.05094  -0.0110   0.0640   1.0000
  13.000   1.2518   0.05875   0.05348  -0.0065   0.0636   1.0000
  13.250   1.2258   0.06188   0.05689  -0.0030   0.0631   1.0000
  13.500   1.1967   0.06599   0.06127  -0.0009   0.0628   1.0000
  13.750   1.1644   0.07124   0.06676  -0.0003   0.0628   1.0000
  14.000   1.1276   0.07776   0.07350  -0.0014   0.0630   1.0000
  14.250   1.0877   0.08590   0.08184  -0.0046   0.0633   1.0000
  14.500   1.0455   0.09622   0.09232  -0.0099   0.0638   1.0000
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