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RAE 103 AIRFOIL (rae103-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RAE 103 AIRFOIL (rae103-il)
Reynolds number: 50,000
Max Cl/Cd: 27.08 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae103-il-50000-n5.txt
Download as CSV file: xf-rae103-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6510   0.09714   0.08996  -0.0171   1.0000   0.0470
 -10.500  -0.6622   0.09001   0.08286  -0.0218   1.0000   0.0465
 -10.250  -0.6779   0.08346   0.07632  -0.0260   1.0000   0.0457
 -10.000  -0.6976   0.07758   0.07040  -0.0292   1.0000   0.0447
  -9.750  -0.7181   0.07275   0.06549  -0.0305   1.0000   0.0442
  -9.500  -0.7369   0.06883   0.06146  -0.0297   1.0000   0.0440
  -9.250  -0.7508   0.06505   0.05750  -0.0285   1.0000   0.0439
  -9.000  -0.7601   0.06134   0.05355  -0.0271   1.0000   0.0443
  -8.750  -0.7651   0.05771   0.04963  -0.0254   1.0000   0.0450
  -8.500  -0.7664   0.05412   0.04569  -0.0236   1.0000   0.0457
  -8.250  -0.7640   0.05053   0.04169  -0.0216   1.0000   0.0462
  -8.000  -0.7574   0.04708   0.03781  -0.0197   1.0000   0.0468
  -7.750  -0.7472   0.04378   0.03402  -0.0178   1.0000   0.0476
  -7.500  -0.7332   0.04076   0.03046  -0.0160   1.0000   0.0491
  -7.250  -0.7166   0.03813   0.02750  -0.0146   1.0000   0.0519
  -7.000  -0.6980   0.03612   0.02536  -0.0136   1.0000   0.0559
  -6.750  -0.6753   0.03389   0.02276  -0.0126   1.0000   0.0592
  -6.500  -0.6495   0.03183   0.02034  -0.0116   1.0000   0.0634
  -6.250  -0.6276   0.03022   0.01879  -0.0108   1.0000   0.0705
  -6.000  -0.6031   0.02864   0.01704  -0.0097   1.0000   0.0780
  -5.750  -0.5825   0.02731   0.01563  -0.0083   1.0000   0.0879
  -5.500  -0.5647   0.02606   0.01436  -0.0067   1.0000   0.1021
  -5.250  -0.5495   0.02470   0.01307  -0.0047   1.0000   0.1193
  -5.000  -0.5367   0.02329   0.01190  -0.0025   1.0000   0.1520
  -4.750  -0.5272   0.02160   0.01075  -0.0001   1.0000   0.2188
  -4.500  -0.5239   0.01964   0.00995   0.0035   1.0000   0.3824
  -4.250  -0.5164   0.01907   0.01033   0.0087   1.0000   0.5763
  -4.000  -0.5040   0.01915   0.01049   0.0131   1.0000   0.6603
  -3.750  -0.4891   0.01938   0.01066   0.0172   1.0000   0.7174
  -3.500  -0.4715   0.01972   0.01093   0.0210   1.0000   0.7633
  -3.250  -0.4497   0.02008   0.01118   0.0240   1.0000   0.8009
  -3.000  -0.4214   0.02042   0.01134   0.0255   1.0000   0.8307
  -2.750  -0.3941   0.02055   0.01124   0.0263   1.0000   0.8544
  -2.500  -0.3602   0.02064   0.01113   0.0255   1.0000   0.8718
  -2.250  -0.3275   0.02064   0.01094   0.0245   1.0000   0.8868
  -2.000  -0.2958   0.02058   0.01072   0.0233   1.0000   0.9005
  -1.750  -0.2645   0.02050   0.01047   0.0220   1.0000   0.9135
  -1.500  -0.2279   0.02044   0.01027   0.0195   1.0000   0.9244
  -1.250  -0.1910   0.02036   0.01009   0.0168   1.0000   0.9347
  -1.000  -0.1572   0.02030   0.00992   0.0145   1.0000   0.9460
  -0.750  -0.1243   0.02025   0.00981   0.0122   1.0000   0.9579
  -0.500  -0.0906   0.02022   0.00974   0.0097   1.0000   0.9702
  -0.250  -0.0476   0.02019   0.00967   0.0053   0.9953   0.9789
   0.000   0.0001   0.02018   0.00965   0.0000   0.9868   0.9868
   0.250   0.0477   0.02019   0.00966  -0.0052   0.9789   0.9953
   0.500   0.0907   0.02022   0.00974  -0.0097   0.9702   1.0000
   0.750   0.1242   0.02025   0.00981  -0.0122   0.9579   1.0000
   1.000   0.1572   0.02030   0.00992  -0.0145   0.9461   1.0000
   1.250   0.1910   0.02036   0.01009  -0.0168   0.9347   1.0000
   1.500   0.2280   0.02044   0.01027  -0.0195   0.9244   1.0000
   1.750   0.2645   0.02050   0.01047  -0.0220   0.9135   1.0000
   2.000   0.2958   0.02058   0.01072  -0.0233   0.9005   1.0000
   2.250   0.3275   0.02064   0.01094  -0.0244   0.8868   1.0000
   2.500   0.3603   0.02064   0.01113  -0.0255   0.8718   1.0000
   2.750   0.3940   0.02055   0.01124  -0.0263   0.8543   1.0000
   3.000   0.4214   0.02042   0.01134  -0.0254   0.8307   1.0000
   3.250   0.4497   0.02008   0.01118  -0.0240   0.8009   1.0000
   3.500   0.4715   0.01972   0.01093  -0.0210   0.7633   1.0000
   3.750   0.4891   0.01937   0.01066  -0.0171   0.7173   1.0000
   4.000   0.5040   0.01915   0.01049  -0.0130   0.6601   1.0000
   4.250   0.5164   0.01907   0.01033  -0.0087   0.5765   1.0000
   4.500   0.5238   0.01964   0.00995  -0.0035   0.3819   1.0000
   4.750   0.5271   0.02161   0.01075   0.0001   0.2182   1.0000
   5.000   0.5367   0.02330   0.01191   0.0025   0.1516   1.0000
   5.250   0.5495   0.02471   0.01306   0.0047   0.1189   1.0000
   5.500   0.5647   0.02605   0.01436   0.0067   0.1020   1.0000
   5.750   0.5825   0.02732   0.01564   0.0083   0.0878   1.0000
   6.000   0.6031   0.02865   0.01704   0.0097   0.0779   1.0000
   6.250   0.6277   0.03023   0.01879   0.0108   0.0707   1.0000
   6.500   0.6495   0.03186   0.02036   0.0116   0.0632   1.0000
   6.750   0.6753   0.03388   0.02275   0.0126   0.0593   1.0000
   7.000   0.6981   0.03612   0.02536   0.0136   0.0558   1.0000
   7.250   0.7167   0.03812   0.02749   0.0147   0.0520   1.0000
   7.500   0.7332   0.04075   0.03045   0.0160   0.0491   1.0000
   7.750   0.7472   0.04381   0.03405   0.0178   0.0476   1.0000
   8.000   0.7575   0.04707   0.03779   0.0197   0.0468   1.0000
   8.250   0.7640   0.05055   0.04172   0.0216   0.0462   1.0000
   8.500   0.7666   0.05411   0.04568   0.0236   0.0458   1.0000
   8.750   0.7652   0.05775   0.04967   0.0254   0.0451   1.0000
   9.000   0.7601   0.06138   0.05360   0.0270   0.0444   1.0000
   9.250   0.7508   0.06512   0.05758   0.0285   0.0440   1.0000
   9.500   0.7368   0.06887   0.06150   0.0297   0.0439   1.0000
   9.750   0.7176   0.07287   0.06561   0.0304   0.0442   1.0000
  10.000   0.6978   0.07763   0.07044   0.0291   0.0447   1.0000
  10.250   0.6787   0.08346   0.07632   0.0260   0.0458   1.0000
  10.500   0.6623   0.09013   0.08298   0.0216   0.0464   1.0000
  10.750   0.6523   0.09702   0.08984   0.0172   0.0472   1.0000
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