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RAE(NPL) 5213 AIRFOIL (rae5213-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: RAE(NPL) 5213 AIRFOIL (rae5213-il)
Reynolds number: 200,000
Max Cl/Cd: 49.64 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae5213-il-200000.txt
Download as CSV file: xf-rae5213-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE(NPL) 5213 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  -0.5018   0.10520   0.10125  -0.0186   1.0000   0.0515
 -10.000  -0.5160   0.09863   0.09475  -0.0253   1.0000   0.0535
  -9.750  -0.5516   0.08785   0.08400  -0.0386   1.0000   0.0540
  -9.500  -0.5187   0.08933   0.08552  -0.0290   1.0000   0.0550
  -9.250  -0.5109   0.08690   0.08311  -0.0284   1.0000   0.0560
  -9.000  -0.5098   0.08324   0.07950  -0.0298   1.0000   0.0576
  -8.750  -0.5170   0.07793   0.07423  -0.0336   1.0000   0.0589
  -8.500  -0.5359   0.07120   0.06753  -0.0397   1.0000   0.0592
  -8.250  -0.5601   0.06585   0.06211  -0.0438   1.0000   0.0599
  -7.750  -0.5908   0.05610   0.05192  -0.0466   1.0000   0.0632
  -7.500  -0.5800   0.05354   0.04940  -0.0456   1.0000   0.0643
  -7.250  -0.5722   0.05103   0.04685  -0.0447   1.0000   0.0663
  -7.000  -0.5782   0.04753   0.04273  -0.0441   1.0000   0.0721
  -6.750  -0.5647   0.04456   0.03990  -0.0431   1.0000   0.0735
  -6.500  -0.5524   0.04259   0.03792  -0.0417   1.0000   0.0765
  -6.250  -0.5449   0.03998   0.03499  -0.0406   1.0000   0.0841
  -6.000  -0.5291   0.02918   0.02273  -0.0379   1.0000   0.0456
  -5.750  -0.5105   0.02525   0.01789  -0.0359   1.0000   0.0413
  -5.500  -0.4911   0.02341   0.01605  -0.0349   1.0000   0.0422
  -5.250  -0.4714   0.02244   0.01507  -0.0338   1.0000   0.0442
  -5.000  -0.4505   0.02113   0.01353  -0.0325   1.0000   0.0454
  -4.750  -0.4289   0.01989   0.01209  -0.0313   1.0000   0.0462
  -4.500  -0.4074   0.01879   0.01083  -0.0301   1.0000   0.0475
  -4.250  -0.3865   0.01795   0.01009  -0.0292   1.0000   0.0500
  -4.000  -0.3636   0.01733   0.00941  -0.0285   0.9997   0.0525
  -3.750  -0.3258   0.01636   0.00844  -0.0305   0.9959   0.0551
  -3.500  -0.2880   0.01570   0.00787  -0.0328   0.9914   0.0599
  -3.250  -0.2498   0.01492   0.00714  -0.0351   0.9868   0.0643
  -3.000  -0.2117   0.01440   0.00665  -0.0374   0.9818   0.0715
  -2.750  -0.1731   0.01364   0.00599  -0.0399   0.9766   0.0852
  -2.500  -0.1412   0.01113   0.00547  -0.0425   0.9728   0.5075
  -2.250  -0.1066   0.01127   0.00584  -0.0433   0.9655   0.6117
  -2.000  -0.0691   0.01147   0.00604  -0.0448   0.9596   0.6462
  -1.750  -0.0332   0.01168   0.00627  -0.0459   0.9526   0.6765
  -1.500   0.0054   0.01198   0.00668  -0.0469   0.9482   0.7118
  -1.250   0.0340   0.01215   0.00696  -0.0460   0.9395   0.7362
  -1.000   0.0752   0.01209   0.00690  -0.0482   0.9355   0.7491
  -0.750   0.1082   0.01200   0.00678  -0.0490   0.9275   0.7558
  -0.500   0.1485   0.01180   0.00653  -0.0512   0.9208   0.7626
  -0.250   0.1816   0.01157   0.00633  -0.0516   0.9104   0.7678
   0.000   0.2193   0.01129   0.00602  -0.0528   0.9017   0.7738
   0.250   0.2487   0.01107   0.00577  -0.0524   0.8868   0.7801
   0.500   0.2765   0.01076   0.00545  -0.0513   0.8682   0.7853
   0.750   0.3035   0.01054   0.00518  -0.0501   0.8481   0.7916
   1.000   0.3300   0.01040   0.00500  -0.0492   0.8289   0.7977
   1.250   0.3559   0.01028   0.00488  -0.0482   0.8110   0.8035
   1.500   0.3822   0.01020   0.00478  -0.0474   0.7911   0.8102
   1.750   0.4080   0.01013   0.00469  -0.0465   0.7686   0.8163
   2.000   0.4334   0.01007   0.00460  -0.0454   0.7435   0.8230
   2.250   0.4592   0.01007   0.00453  -0.0445   0.7123   0.8304
   2.500   0.4829   0.01006   0.00445  -0.0430   0.6718   0.8372
   2.750   0.5058   0.01019   0.00437  -0.0415   0.6053   0.8457
   3.000   0.5214   0.01083   0.00433  -0.0387   0.4538   0.8540
   3.250   0.5321   0.01247   0.00480  -0.0362   0.2312   0.8644
   3.500   0.5513   0.01320   0.00521  -0.0347   0.1802   0.8757
   3.750   0.5729   0.01370   0.00560  -0.0335   0.1617   0.8895
   4.000   0.5963   0.01407   0.00597  -0.0326   0.1498   0.9078
   4.250   0.6236   0.01450   0.00643  -0.0325   0.1399   0.9379
   4.500   0.6576   0.01525   0.00707  -0.0343   0.1302   1.0000
   4.750   0.6868   0.01572   0.00753  -0.0349   0.1226   1.0000
   5.000   0.7134   0.01656   0.00824  -0.0352   0.1154   1.0000
   5.250   0.7410   0.01702   0.00872  -0.0353   0.1086   1.0000
   5.500   0.7667   0.01799   0.00953  -0.0353   0.1023   1.0000
   5.750   0.7934   0.01846   0.01008  -0.0351   0.0966   1.0000
   6.000   0.8188   0.01939   0.01086  -0.0350   0.0911   1.0000
   6.250   0.8447   0.02004   0.01162  -0.0347   0.0859   1.0000
   6.500   0.8698   0.02070   0.01221  -0.0344   0.0810   1.0000
   6.750   0.8951   0.02174   0.01332  -0.0341   0.0765   1.0000
   7.000   0.9200   0.02243   0.01404  -0.0337   0.0724   1.0000
   7.250   0.9448   0.02361   0.01518  -0.0334   0.0690   1.0000
   7.500   0.9690   0.02440   0.01613  -0.0328   0.0655   1.0000
   7.750   0.9932   0.02519   0.01691  -0.0324   0.0629   1.0000
   8.000   1.0172   0.02673   0.01852  -0.0319   0.0609   1.0000
   8.250   1.0397   0.02821   0.02028  -0.0311   0.0589   1.0000
   8.500   1.0622   0.02956   0.02178  -0.0304   0.0571   1.0000
   8.750   1.0847   0.03063   0.02289  -0.0299   0.0556   1.0000
   9.000   1.1063   0.03252   0.02479  -0.0295   0.0543   1.0000
   9.250   1.1213   0.03477   0.02753  -0.0279   0.0531   1.0000
   9.500   1.1343   0.03762   0.03081  -0.0263   0.0523   1.0000
   9.750   1.1435   0.04090   0.03451  -0.0245   0.0518   1.0000
  10.000   1.1473   0.04474   0.03879  -0.0224   0.0515   1.0000
  10.250   1.1431   0.04933   0.04383  -0.0200   0.0516   1.0000
  10.500   1.1314   0.05429   0.04920  -0.0175   0.0519   1.0000
  10.750   1.1104   0.05938   0.05465  -0.0147   0.0523   1.0000
  11.000   1.0851   0.06366   0.05916  -0.0118   0.0527   1.0000
  11.250   1.0594   0.06825   0.06392  -0.0106   0.0531   1.0000
  11.500   1.0344   0.07342   0.06925  -0.0113   0.0535   1.0000
  11.750   1.0132   0.07910   0.07503  -0.0133   0.0538   1.0000
  12.000   1.0003   0.08464   0.08063  -0.0157   0.0541   1.0000
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