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RAE 103 AIRFOIL (rae103-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RAE 103 AIRFOIL (rae103-il)
Reynolds number: 100,000
Max Cl/Cd: 36.48 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae103-il-100000-n5.txt
Download as CSV file: xf-rae103-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 103 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.6653   0.09185   0.08676  -0.0171   1.0000   0.0254
 -10.750  -0.6826   0.08198   0.07691  -0.0239   1.0000   0.0244
 -10.500  -0.7092   0.07326   0.06814  -0.0299   1.0000   0.0236
 -10.250  -0.7376   0.06654   0.06127  -0.0330   1.0000   0.0229
 -10.000  -0.7603   0.06194   0.05651  -0.0332   1.0000   0.0227
  -9.750  -0.7825   0.05795   0.05231  -0.0312   1.0000   0.0225
  -9.500  -0.7932   0.05487   0.04904  -0.0290   1.0000   0.0228
  -9.250  -0.7988   0.05176   0.04569  -0.0270   1.0000   0.0232
  -9.000  -0.8005   0.04878   0.04244  -0.0249   1.0000   0.0240
  -8.750  -0.8003   0.04551   0.03881  -0.0226   1.0000   0.0246
  -8.500  -0.7970   0.04215   0.03504  -0.0203   1.0000   0.0249
  -8.250  -0.7899   0.03891   0.03133  -0.0180   1.0000   0.0253
  -8.000  -0.7789   0.03602   0.02799  -0.0159   1.0000   0.0259
  -7.750  -0.7645   0.03336   0.02491  -0.0140   1.0000   0.0267
  -7.500  -0.7472   0.03115   0.02228  -0.0124   1.0000   0.0279
  -7.250  -0.7292   0.02908   0.01999  -0.0111   1.0000   0.0297
  -7.000  -0.7107   0.02769   0.01853  -0.0099   1.0000   0.0321
  -6.750  -0.6903   0.02612   0.01680  -0.0087   1.0000   0.0339
  -6.500  -0.6698   0.02464   0.01512  -0.0073   1.0000   0.0361
  -6.250  -0.6497   0.02350   0.01382  -0.0059   1.0000   0.0390
  -6.000  -0.6331   0.02225   0.01263  -0.0043   1.0000   0.0432
  -5.750  -0.6156   0.02125   0.01156  -0.0025   1.0000   0.0473
  -5.500  -0.5992   0.02027   0.01050  -0.0004   1.0000   0.0517
  -5.250  -0.5828   0.01946   0.00970   0.0014   1.0000   0.0599
  -5.000  -0.5672   0.01861   0.00883   0.0035   1.0000   0.0689
  -4.750  -0.5516   0.01784   0.00810   0.0055   1.0000   0.0835
  -4.500  -0.5367   0.01704   0.00746   0.0076   1.0000   0.1097
  -4.250  -0.5235   0.01616   0.00688   0.0098   1.0000   0.1625
  -4.000  -0.5133   0.01506   0.00636   0.0123   1.0000   0.2691
  -3.750  -0.5064   0.01388   0.00604   0.0156   1.0000   0.4281
  -3.500  -0.4790   0.01338   0.00617   0.0157   0.9912   0.5952
  -3.250  -0.4461   0.01335   0.00623   0.0150   0.9830   0.6605
  -3.000  -0.4146   0.01338   0.00625   0.0146   0.9738   0.7035
  -2.750  -0.3820   0.01343   0.00625   0.0141   0.9656   0.7380
  -2.500  -0.3485   0.01350   0.00629   0.0134   0.9580   0.7663
  -2.250  -0.3155   0.01357   0.00631   0.0128   0.9502   0.7884
  -2.000  -0.2797   0.01360   0.00628   0.0115   0.9436   0.8056
  -1.750  -0.2458   0.01360   0.00618   0.0104   0.9354   0.8187
  -1.500  -0.2094   0.01358   0.00609   0.0087   0.9285   0.8299
  -1.250  -0.1771   0.01354   0.00599   0.0078   0.9197   0.8408
  -1.000  -0.1388   0.01354   0.00592   0.0057   0.9136   0.8485
  -0.750  -0.1062   0.01351   0.00585   0.0047   0.9046   0.8577
  -0.500  -0.0684   0.01349   0.00580   0.0027   0.8984   0.8657
  -0.250  -0.0354   0.01349   0.00579   0.0016   0.8894   0.8738
   0.000   0.0000   0.01347   0.00576   0.0000   0.8824   0.8824
   0.250   0.0354   0.01349   0.00579  -0.0016   0.8738   0.8894
   0.500   0.0684   0.01349   0.00580  -0.0027   0.8656   0.8984
   0.750   0.1062   0.01351   0.00586  -0.0047   0.8577   0.9046
   1.000   0.1388   0.01354   0.00592  -0.0057   0.8485   0.9137
   1.250   0.1772   0.01354   0.00599  -0.0078   0.8408   0.9198
   1.500   0.2095   0.01358   0.00609  -0.0087   0.8299   0.9285
   1.750   0.2458   0.01360   0.00618  -0.0104   0.8187   0.9354
   2.000   0.2797   0.01360   0.00628  -0.0115   0.8055   0.9436
   2.250   0.3155   0.01357   0.00631  -0.0128   0.7883   0.9502
   2.500   0.3485   0.01350   0.00629  -0.0134   0.7663   0.9580
   2.750   0.3820   0.01343   0.00625  -0.0141   0.7380   0.9657
   3.000   0.4146   0.01337   0.00625  -0.0146   0.7030   0.9739
   3.250   0.4460   0.01335   0.00622  -0.0150   0.6603   0.9830
   3.500   0.4789   0.01338   0.00617  -0.0157   0.5941   0.9912
   3.750   0.5063   0.01388   0.00604  -0.0155   0.4271   1.0000
   4.000   0.5131   0.01507   0.00637  -0.0123   0.2676   1.0000
   4.250   0.5235   0.01616   0.00688  -0.0098   0.1625   1.0000
   4.500   0.5367   0.01705   0.00746  -0.0076   0.1097   1.0000
   4.750   0.5515   0.01784   0.00811  -0.0055   0.0836   1.0000
   5.000   0.5672   0.01861   0.00883  -0.0034   0.0688   1.0000
   5.250   0.5828   0.01947   0.00971  -0.0014   0.0599   1.0000
   5.500   0.5992   0.02027   0.01050   0.0005   0.0518   1.0000
   5.750   0.6155   0.02126   0.01157   0.0025   0.0473   1.0000
   6.000   0.6331   0.02225   0.01263   0.0043   0.0431   1.0000
   6.250   0.6497   0.02350   0.01381   0.0059   0.0389   1.0000
   6.500   0.6698   0.02465   0.01513   0.0073   0.0360   1.0000
   6.750   0.6903   0.02611   0.01679   0.0087   0.0340   1.0000
   7.000   0.7107   0.02768   0.01853   0.0099   0.0320   1.0000
   7.250   0.7296   0.02912   0.02005   0.0111   0.0300   1.0000
   7.500   0.7472   0.03117   0.02229   0.0124   0.0279   1.0000
   7.750   0.7645   0.03339   0.02493   0.0141   0.0267   1.0000
   8.000   0.7790   0.03600   0.02797   0.0159   0.0259   1.0000
   8.250   0.7899   0.03894   0.03136   0.0180   0.0253   1.0000
   8.500   0.7972   0.04212   0.03501   0.0202   0.0250   1.0000
   8.750   0.8003   0.04553   0.03883   0.0226   0.0246   1.0000
   9.000   0.8002   0.04887   0.04253   0.0249   0.0241   1.0000
   9.250   0.7982   0.05191   0.04585   0.0270   0.0233   1.0000
   9.500   0.7936   0.05483   0.04900   0.0290   0.0227   1.0000
   9.750   0.7946   0.05653   0.05075   0.0304   0.0217   1.0000
  10.000   0.7635   0.06155   0.05610   0.0332   0.0225   1.0000
  10.250   0.7339   0.06722   0.06198   0.0327   0.0233   1.0000
  10.500   0.7105   0.07310   0.06797   0.0299   0.0234   1.0000
  10.750   0.6832   0.08205   0.07698   0.0238   0.0248   1.0000
  11.000   0.6656   0.09200   0.08692   0.0169   0.0255   1.0000
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