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RAE(NPL) 5213 AIRFOIL (rae5213-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RAE(NPL) 5213 AIRFOIL (rae5213-il)
Reynolds number: 50,000
Max Cl/Cd: 29.21 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae5213-il-50000-n5.txt
Download as CSV file: xf-rae5213-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5253   0.11125   0.10339  -0.0204   1.0000   0.0624
 -10.250  -0.5175   0.10762   0.09975  -0.0207   1.0000   0.0606
 -10.000  -0.5148   0.10344   0.09562  -0.0221   1.0000   0.0591
  -9.500  -0.5395   0.08838   0.08067  -0.0334   1.0000   0.0539
  -9.250  -0.5405   0.08399   0.07632  -0.0353   1.0000   0.0533
  -9.000  -0.5484   0.07902   0.07139  -0.0381   1.0000   0.0528
  -8.750  -0.5610   0.07437   0.06676  -0.0406   1.0000   0.0522
  -8.500  -0.5734   0.06987   0.06222  -0.0427   1.0000   0.0516
  -8.250  -0.5829   0.06543   0.05765  -0.0441   1.0000   0.0511
  -8.000  -0.5884   0.06121   0.05325  -0.0449   1.0000   0.0507
  -7.750  -0.5900   0.05720   0.04900  -0.0452   1.0000   0.0509
  -7.500  -0.5876   0.05348   0.04498  -0.0451   1.0000   0.0515
  -7.250  -0.5818   0.04994   0.04106  -0.0448   1.0000   0.0522
  -7.000  -0.5731   0.04650   0.03716  -0.0442   1.0000   0.0531
  -6.750  -0.5610   0.04327   0.03340  -0.0434   1.0000   0.0538
  -6.500  -0.5452   0.04056   0.03041  -0.0426   1.0000   0.0544
  -6.250  -0.5275   0.03828   0.02798  -0.0417   1.0000   0.0555
  -6.000  -0.5091   0.03632   0.02583  -0.0407   1.0000   0.0576
  -5.750  -0.4896   0.03434   0.02351  -0.0397   1.0000   0.0601
  -5.500  -0.4687   0.03244   0.02117  -0.0385   1.0000   0.0620
  -5.250  -0.4483   0.03079   0.01954  -0.0373   1.0000   0.0641
  -5.000  -0.4276   0.02947   0.01815  -0.0360   1.0000   0.0675
  -4.750  -0.4061   0.02823   0.01668  -0.0345   1.0000   0.0710
  -4.500  -0.3862   0.02702   0.01555  -0.0328   1.0000   0.0738
  -4.250  -0.3666   0.02607   0.01457  -0.0312   1.0000   0.0783
  -4.000  -0.3474   0.02515   0.01361  -0.0296   1.0000   0.0837
  -3.750  -0.3285   0.02428   0.01274  -0.0281   1.0000   0.0897
  -3.500  -0.3094   0.02340   0.01188  -0.0269   1.0000   0.0982
  -3.250  -0.2891   0.02250   0.01102  -0.0260   1.0000   0.1113
  -3.000  -0.2681   0.02147   0.01012  -0.0255   1.0000   0.1374
  -2.750  -0.2475   0.01897   0.00924  -0.0263   1.0000   0.3594
  -2.500  -0.2383   0.01902   0.01018  -0.0214   1.0000   0.5973
  -2.250  -0.2267   0.01947   0.01067  -0.0172   1.0000   0.6722
  -2.000  -0.2207   0.01984   0.01117  -0.0114   1.0000   0.7293
  -1.750  -0.2176   0.02002   0.01145  -0.0049   1.0000   0.7792
  -1.500  -0.2097   0.01997   0.01140  -0.0001   1.0000   0.8126
  -1.250  -0.1828   0.01993   0.01122  -0.0001   0.9951   0.8282
  -1.000  -0.1470   0.01996   0.01108  -0.0021   0.9867   0.8395
  -0.750  -0.1111   0.02000   0.01098  -0.0042   0.9780   0.8511
  -0.500  -0.0751   0.02005   0.01091  -0.0063   0.9692   0.8629
  -0.250  -0.0375   0.02011   0.01089  -0.0085   0.9606   0.8744
   0.000  -0.0003   0.02016   0.01090  -0.0108   0.9512   0.8865
   0.250   0.0368   0.02021   0.01092  -0.0130   0.9414   0.8997
   0.500   0.0811   0.02032   0.01102  -0.0166   0.9333   0.9126
   0.750   0.1219   0.02039   0.01111  -0.0195   0.9228   0.9274
   1.000   0.1686   0.02050   0.01126  -0.0236   0.9134   0.9437
   1.250   0.2190   0.02059   0.01141  -0.0284   0.9037   0.9634
   1.500   0.2622   0.02066   0.01154  -0.0320   0.8914   1.0000
   1.750   0.3022   0.02075   0.01169  -0.0347   0.8792   1.0000
   2.000   0.3439   0.02063   0.01164  -0.0370   0.8610   1.0000
   2.250   0.3925   0.01976   0.01081  -0.0382   0.8228   1.0000
   2.500   0.4330   0.01885   0.00986  -0.0376   0.7754   1.0000
   2.750   0.4618   0.01861   0.00960  -0.0367   0.7386   1.0000
   3.000   0.4888   0.01852   0.00949  -0.0357   0.6989   1.0000
   3.250   0.5152   0.01846   0.00939  -0.0345   0.6482   1.0000
   3.500   0.5394   0.01854   0.00924  -0.0327   0.5655   1.0000
   3.750   0.5597   0.01916   0.00905  -0.0303   0.4208   1.0000
   4.000   0.5748   0.02065   0.00956  -0.0285   0.2905   1.0000
   4.250   0.5941   0.02199   0.01038  -0.0277   0.2348   1.0000
   4.500   0.6161   0.02312   0.01126  -0.0272   0.2061   1.0000
   4.750   0.6396   0.02415   0.01213  -0.0267   0.1875   1.0000
   5.000   0.6639   0.02515   0.01303  -0.0264   0.1730   1.0000
   5.250   0.6892   0.02621   0.01398  -0.0261   0.1616   1.0000
   5.500   0.7160   0.02720   0.01502  -0.0260   0.1508   1.0000
   5.750   0.7432   0.02833   0.01613  -0.0259   0.1419   1.0000
   6.000   0.7704   0.02949   0.01730  -0.0258   0.1335   1.0000
   6.250   0.7978   0.03080   0.01866  -0.0257   0.1259   1.0000
   6.500   0.8240   0.03210   0.01999  -0.0255   0.1189   1.0000
   6.750   0.8497   0.03362   0.02163  -0.0253   0.1125   1.0000
   7.000   0.8742   0.03511   0.02326  -0.0250   0.1064   1.0000
   7.250   0.8980   0.03680   0.02498  -0.0247   0.1014   1.0000
   7.500   0.9198   0.03869   0.02723  -0.0241   0.0962   1.0000
   7.750   0.9416   0.04040   0.02901  -0.0237   0.0920   1.0000
   8.000   0.9610   0.04271   0.03159  -0.0230   0.0887   1.0000
   8.250   0.9766   0.04528   0.03462  -0.0219   0.0851   1.0000
   8.500   0.9933   0.04748   0.03704  -0.0211   0.0820   1.0000
   8.750   1.0104   0.04970   0.03935  -0.0205   0.0799   1.0000
   9.000   1.0182   0.05306   0.04314  -0.0192   0.0782   1.0000
   9.250   1.0185   0.05690   0.04752  -0.0176   0.0764   1.0000
   9.500   1.0162   0.06070   0.05172  -0.0162   0.0749   1.0000
   9.750   1.0113   0.06445   0.05579  -0.0150   0.0736   1.0000
  10.000   1.0018   0.06841   0.06001  -0.0138   0.0728   1.0000
  10.250   0.9841   0.07260   0.06442  -0.0126   0.0724   1.0000
  10.500   0.9553   0.07797   0.07000  -0.0128   0.0726   1.0000
  10.750   0.9155   0.08590   0.07811  -0.0165   0.0732   1.0000
  11.000   0.8695   0.09792   0.09023  -0.0251   0.0744   1.0000
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