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RAE 5215 AIRFOIL (rae5215-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: RAE 5215 AIRFOIL (rae5215-il)
Reynolds number: 200,000
Max Cl/Cd: 43.76 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae5215-il-200000.txt
Download as CSV file: xf-rae5215-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 5215 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4266   0.11178   0.10812  -0.0153   1.0000   0.0525
 -10.500  -0.4358   0.10679   0.10314  -0.0184   1.0000   0.0544
 -10.250  -0.4653   0.09892   0.09531  -0.0259   1.0000   0.0552
 -10.000  -0.4515   0.09597   0.09238  -0.0233   1.0000   0.0559
  -9.750  -0.4404   0.09356   0.08998  -0.0220   1.0000   0.0569
  -9.500  -0.4374   0.09002   0.08645  -0.0224   1.0000   0.0582
  -9.250  -0.4398   0.08560   0.08206  -0.0238   1.0000   0.0598
  -9.000  -0.4516   0.07954   0.07603  -0.0273   1.0000   0.0617
  -8.750  -0.5744   0.08048   0.07683  -0.0284   1.0000   0.0567
  -8.500  -0.5764   0.07582   0.07218  -0.0317   1.0000   0.0575
  -8.250  -0.5860   0.07002   0.06636  -0.0377   1.0000   0.0582
  -8.000  -0.5899   0.06505   0.06129  -0.0416   1.0000   0.0596
  -7.750  -0.6165   0.05831   0.05373  -0.0480   1.0000   0.0636
  -7.500  -0.5995   0.05431   0.04997  -0.0474   1.0000   0.0647
  -7.250  -0.5864   0.05168   0.04738  -0.0468   1.0000   0.0661
  -7.000  -0.5755   0.04897   0.04455  -0.0465   1.0000   0.0688
  -6.750  -0.5697   0.04503   0.04017  -0.0468   1.0000   0.0743
  -6.500  -0.5576   0.03256   0.02608  -0.0457   1.0000   0.0425
  -6.250  -0.5388   0.02996   0.02333  -0.0446   1.0000   0.0413
  -6.000  -0.5194   0.02755   0.02047  -0.0435   1.0000   0.0417
  -5.750  -0.4989   0.02553   0.01809  -0.0424   1.0000   0.0419
  -5.500  -0.4776   0.02369   0.01596  -0.0413   1.0000   0.0421
  -5.250  -0.4569   0.02203   0.01441  -0.0405   1.0000   0.0438
  -5.000  -0.4350   0.02103   0.01331  -0.0396   1.0000   0.0458
  -4.750  -0.4117   0.01981   0.01190  -0.0386   1.0000   0.0468
  -4.500  -0.3880   0.01891   0.01079  -0.0377   1.0000   0.0481
  -4.250  -0.3641   0.01772   0.00970  -0.0373   1.0000   0.0501
  -4.000  -0.3404   0.01715   0.00914  -0.0367   1.0000   0.0534
  -3.750  -0.3152   0.01640   0.00837  -0.0364   1.0000   0.0562
  -3.500  -0.2895   0.01580   0.00786  -0.0364   1.0000   0.0601
  -3.250  -0.2631   0.01530   0.00734  -0.0363   1.0000   0.0637
  -3.000  -0.2355   0.01465   0.00679  -0.0368   1.0000   0.0690
  -2.750  -0.2075   0.01415   0.00634  -0.0373   1.0000   0.0778
  -2.500  -0.1774   0.01350   0.00585  -0.0382   1.0000   0.1051
  -2.250  -0.1372   0.01147   0.00591  -0.0420   1.0000   0.5920
  -2.000  -0.1048   0.01175   0.00621  -0.0428   0.9973   0.6349
  -1.750  -0.0682   0.01204   0.00651  -0.0443   0.9940   0.6634
  -1.500  -0.0361   0.01238   0.00692  -0.0447   0.9892   0.6961
  -1.250  -0.0013   0.01274   0.00740  -0.0453   0.9851   0.7293
  -1.000   0.0345   0.01282   0.00753  -0.0464   0.9775   0.7483
  -0.750   0.0785   0.01271   0.00742  -0.0493   0.9701   0.7569
  -0.500   0.1234   0.01254   0.00721  -0.0526   0.9624   0.7636
  -0.250   0.1727   0.01215   0.00684  -0.0562   0.9513   0.7689
   0.000   0.2214   0.01162   0.00630  -0.0593   0.9363   0.7751
   0.250   0.2572   0.01125   0.00591  -0.0599   0.9207   0.7811
   0.500   0.2863   0.01096   0.00566  -0.0591   0.9061   0.7864
   0.750   0.3147   0.01077   0.00546  -0.0584   0.8925   0.7929
   1.000   0.3414   0.01059   0.00528  -0.0575   0.8767   0.7988
   1.250   0.3661   0.01042   0.00513  -0.0560   0.8571   0.8047
   1.500   0.3914   0.01028   0.00499  -0.0547   0.8310   0.8115
   1.750   0.4159   0.01012   0.00480  -0.0531   0.7976   0.8175
   2.000   0.4393   0.01004   0.00459  -0.0512   0.7379   0.8244
   2.250   0.4526   0.01114   0.00435  -0.0474   0.4519   0.8314
   2.500   0.4679   0.01278   0.00486  -0.0457   0.2373   0.8383
   2.750   0.4925   0.01338   0.00519  -0.0452   0.2016   0.8470
   3.000   0.5165   0.01378   0.00550  -0.0444   0.1845   0.8552
   3.250   0.5423   0.01412   0.00580  -0.0441   0.1723   0.8651
   3.500   0.5661   0.01445   0.00615  -0.0431   0.1630   0.8761
   3.750   0.5898   0.01482   0.00649  -0.0423   0.1548   0.8896
   4.000   0.6134   0.01517   0.00688  -0.0413   0.1475   0.9077
   4.250   0.6377   0.01546   0.00720  -0.0404   0.1405   0.9403
   4.500   0.6692   0.01610   0.00781  -0.0415   0.1332   1.0000
   4.750   0.6997   0.01663   0.00828  -0.0424   0.1257   1.0000
   5.000   0.7287   0.01742   0.00902  -0.0430   0.1185   1.0000
   5.250   0.7573   0.01789   0.00945  -0.0434   0.1114   1.0000
   5.500   0.7849   0.01871   0.01023  -0.0436   0.1050   1.0000
   5.750   0.8125   0.01915   0.01069  -0.0437   0.0987   1.0000
   6.000   0.8392   0.02000   0.01149  -0.0437   0.0932   1.0000
   6.250   0.8660   0.02044   0.01199  -0.0436   0.0875   1.0000
   6.500   0.8920   0.02128   0.01278  -0.0435   0.0826   1.0000
   6.750   0.9181   0.02175   0.01333  -0.0432   0.0774   1.0000
   7.000   0.9436   0.02267   0.01418  -0.0430   0.0736   1.0000
   7.250   0.9691   0.02346   0.01515  -0.0426   0.0695   1.0000
   7.500   0.9944   0.02420   0.01578  -0.0424   0.0666   1.0000
   7.750   1.0187   0.02541   0.01722  -0.0418   0.0634   1.0000
   8.000   1.0430   0.02626   0.01815  -0.0414   0.0608   1.0000
   8.250   1.0675   0.02735   0.01916  -0.0411   0.0589   1.0000
   8.500   1.0894   0.02922   0.02136  -0.0402   0.0572   1.0000
   8.750   1.1102   0.03114   0.02361  -0.0393   0.0557   1.0000
   9.000   1.1310   0.03280   0.02546  -0.0385   0.0544   1.0000
   9.250   1.1522   0.03409   0.02682  -0.0378   0.0532   1.0000
   9.500   1.1728   0.03588   0.02862  -0.0373   0.0521   1.0000
   9.750   1.1825   0.03908   0.03238  -0.0353   0.0513   1.0000
  10.000   1.1867   0.04317   0.03705  -0.0330   0.0508   1.0000
  10.250   1.1833   0.04809   0.04252  -0.0305   0.0506   1.0000
  10.500   1.1720   0.05357   0.04847  -0.0277   0.0507   1.0000
  10.750   1.1553   0.05900   0.05428  -0.0251   0.0510   1.0000
  11.000   1.1353   0.06377   0.05931  -0.0225   0.0513   1.0000
  11.250   1.1136   0.06818   0.06390  -0.0205   0.0515   1.0000
  11.500   1.0938   0.07290   0.06875  -0.0200   0.0517   1.0000
  11.750   1.0792   0.07775   0.07369  -0.0205   0.0520   1.0000
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