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RAE 5214 AIRFOIL (rae5214-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: RAE 5214 AIRFOIL (rae5214-il)
Reynolds number: 200,000
Max Cl/Cd: 46.43 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae5214-il-200000.txt
Download as CSV file: xf-rae5214-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5073   0.10529   0.10134  -0.0183   1.0000   0.0513
 -10.000  -0.5223   0.09858   0.09469  -0.0252   1.0000   0.0536
  -9.750  -0.5579   0.08780   0.08395  -0.0385   1.0000   0.0540
  -9.500  -0.5273   0.08878   0.08497  -0.0297   1.0000   0.0550
  -9.250  -0.5175   0.08676   0.08298  -0.0283   1.0000   0.0561
  -9.000  -0.5165   0.08312   0.07936  -0.0297   1.0000   0.0573
  -8.750  -0.5226   0.07805   0.07434  -0.0332   1.0000   0.0584
  -8.500  -0.5430   0.07116   0.06748  -0.0395   1.0000   0.0593
  -8.250  -0.5656   0.06600   0.06227  -0.0432   1.0000   0.0598
  -7.750  -0.5994   0.05615   0.05192  -0.0460   1.0000   0.0632
  -7.500  -0.5883   0.05355   0.04939  -0.0450   1.0000   0.0642
  -7.250  -0.5804   0.05111   0.04693  -0.0440   1.0000   0.0662
  -7.000  -0.5875   0.04790   0.04306  -0.0431   1.0000   0.0721
  -6.750  -0.5742   0.04473   0.04006  -0.0420   1.0000   0.0735
  -6.500  -0.5625   0.04266   0.03798  -0.0406   1.0000   0.0759
  -6.250  -0.5554   0.04019   0.03516  -0.0394   1.0000   0.0840
  -6.000  -0.5391   0.02941   0.02296  -0.0367   1.0000   0.0457
  -5.750  -0.5202   0.02552   0.01814  -0.0348   1.0000   0.0412
  -5.500  -0.5005   0.02346   0.01605  -0.0338   1.0000   0.0421
  -5.250  -0.4805   0.02247   0.01507  -0.0328   1.0000   0.0439
  -5.000  -0.4592   0.02121   0.01359  -0.0316   1.0000   0.0454
  -4.750  -0.4371   0.01995   0.01212  -0.0304   1.0000   0.0462
  -4.500  -0.4147   0.01894   0.01092  -0.0293   1.0000   0.0473
  -4.250  -0.3932   0.01797   0.01007  -0.0285   1.0000   0.0500
  -4.000  -0.3708   0.01732   0.00937  -0.0275   1.0000   0.0525
  -3.750  -0.3482   0.01666   0.00864  -0.0266   1.0000   0.0543
  -3.500  -0.3265   0.01588   0.00800  -0.0258   1.0000   0.0575
  -3.250  -0.2890   0.01540   0.00749  -0.0279   0.9963   0.0619
  -3.000  -0.2527   0.01466   0.00687  -0.0300   0.9926   0.0679
  -2.750  -0.2159   0.01407   0.00634  -0.0321   0.9882   0.0766
  -2.500  -0.1771   0.01331   0.00578  -0.0347   0.9849   0.1120
  -2.250  -0.1502   0.01137   0.00585  -0.0358   0.9803   0.5845
  -2.000  -0.1135   0.01166   0.00620  -0.0372   0.9755   0.6322
  -1.750  -0.0803   0.01190   0.00643  -0.0379   0.9694   0.6607
  -1.500  -0.0453   0.01222   0.00683  -0.0387   0.9641   0.6943
  -1.250  -0.0150   0.01251   0.00723  -0.0383   0.9570   0.7261
  -1.000   0.0214   0.01261   0.00740  -0.0392   0.9512   0.7473
  -0.750   0.0592   0.01251   0.00731  -0.0407   0.9433   0.7564
  -0.500   0.1092   0.01227   0.00701  -0.0447   0.9364   0.7630
  -0.250   0.1516   0.01195   0.00672  -0.0469   0.9267   0.7683
   0.000   0.1998   0.01149   0.00624  -0.0499   0.9164   0.7743
   0.250   0.2367   0.01111   0.00584  -0.0507   0.9024   0.7803
   0.500   0.2661   0.01081   0.00556  -0.0500   0.8867   0.7856
   0.750   0.2944   0.01061   0.00536  -0.0494   0.8710   0.7919
   1.000   0.3224   0.01044   0.00518  -0.0488   0.8548   0.7980
   1.250   0.3489   0.01026   0.00503  -0.0477   0.8366   0.8038
   1.500   0.3760   0.01012   0.00487  -0.0469   0.8155   0.8104
   1.750   0.4019   0.00999   0.00471  -0.0458   0.7890   0.8165
   2.000   0.4269   0.00989   0.00456  -0.0444   0.7546   0.8232
   2.250   0.4518   0.00990   0.00442  -0.0431   0.7015   0.8306
   2.500   0.4713   0.01015   0.00424  -0.0406   0.5854   0.8374
   2.750   0.4812   0.01155   0.00442  -0.0373   0.3424   0.8462
   3.250   0.5203   0.01320   0.00521  -0.0347   0.1953   0.8648
   3.500   0.5422   0.01364   0.00556  -0.0335   0.1771   0.8761
   3.750   0.5654   0.01397   0.00589  -0.0325   0.1642   0.8899
   4.000   0.5890   0.01438   0.00628  -0.0316   0.1538   0.9083
   4.250   0.6170   0.01478   0.00668  -0.0316   0.1443   0.9386
   4.500   0.6528   0.01528   0.00719  -0.0336   0.1349   1.0000
   4.750   0.6809   0.01607   0.00780  -0.0341   0.1270   1.0000
   5.000   0.7098   0.01643   0.00821  -0.0346   0.1194   1.0000
   5.250   0.7366   0.01719   0.00883  -0.0347   0.1125   1.0000
   5.500   0.7638   0.01760   0.00928  -0.0347   0.1057   1.0000
   5.750   0.7898   0.01848   0.01004  -0.0347   0.0998   1.0000
   6.000   0.8161   0.01893   0.01057  -0.0345   0.0939   1.0000
   6.250   0.8416   0.01993   0.01143  -0.0343   0.0884   1.0000
   6.500   0.8672   0.02039   0.01203  -0.0339   0.0830   1.0000
   6.750   0.8923   0.02135   0.01285  -0.0337   0.0785   1.0000
   7.000   0.9173   0.02210   0.01378  -0.0331   0.0740   1.0000
   7.250   0.9421   0.02279   0.01442  -0.0328   0.0704   1.0000
   7.500   0.9664   0.02393   0.01568  -0.0323   0.0669   1.0000
   7.750   0.9904   0.02473   0.01656  -0.0317   0.0637   1.0000
   8.000   1.0148   0.02581   0.01756  -0.0314   0.0616   1.0000
   8.250   1.0373   0.02740   0.01943  -0.0306   0.0595   1.0000
   8.500   1.0593   0.02891   0.02117  -0.0298   0.0577   1.0000
   8.750   1.0814   0.03012   0.02249  -0.0292   0.0561   1.0000
   9.000   1.1037   0.03132   0.02367  -0.0287   0.0547   1.0000
   9.250   1.1212   0.03354   0.02618  -0.0276   0.0534   1.0000
   9.500   1.1344   0.03618   0.02929  -0.0259   0.0524   1.0000
   9.750   1.1443   0.03933   0.03289  -0.0241   0.0517   1.0000
  10.000   1.1489   0.04300   0.03700  -0.0221   0.0513   1.0000
  10.250   1.1454   0.04752   0.04199  -0.0197   0.0512   1.0000
  10.500   1.1313   0.05284   0.04778  -0.0169   0.0514   1.0000
  10.750   1.1084   0.05824   0.05356  -0.0141   0.0518   1.0000
  11.000   1.0773   0.06310   0.05868  -0.0110   0.0523   1.0000
  11.250   1.0466   0.06831   0.06409  -0.0102   0.0527   1.0000
  11.500   1.0175   0.07429   0.07022  -0.0117   0.0532   1.0000
  11.750   0.9957   0.08053   0.07655  -0.0146   0.0536   1.0000
  12.000   0.9791   0.08711   0.08319  -0.0182   0.0539   1.0000
  12.250   0.8477   0.13609   0.13235  -0.0465   0.0784   1.0000
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