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RAE 100 AIRFOIL (rae100-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: RAE 100 AIRFOIL (rae100-il)
Reynolds number: 200,000
Max Cl/Cd: 46.11 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae100-il-200000.txt
Download as CSV file: xf-rae100-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 100 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.7609   0.10135   0.09757  -0.0020   1.0000   0.0414
 -12.250  -0.7712   0.09463   0.09088  -0.0044   1.0000   0.0407
 -12.000  -0.8118   0.08070   0.07690  -0.0140   1.0000   0.0393
 -11.750  -0.8592   0.06815   0.06418  -0.0244   1.0000   0.0382
 -11.500  -0.8993   0.05989   0.05569  -0.0301   1.0000   0.0372
 -11.250  -0.9402   0.05374   0.04923  -0.0312   1.0000   0.0364
 -11.000  -0.9708   0.04944   0.04461  -0.0285   1.0000   0.0360
 -10.750  -0.9868   0.04528   0.04005  -0.0262   1.0000   0.0358
 -10.500  -0.9864   0.04229   0.03677  -0.0244   1.0000   0.0362
 -10.250  -0.9819   0.03948   0.03369  -0.0227   1.0000   0.0368
 -10.000  -0.9739   0.03691   0.03082  -0.0211   1.0000   0.0376
  -9.750  -0.9626   0.03473   0.02835  -0.0195   1.0000   0.0388
  -9.500  -0.9495   0.03279   0.02605  -0.0180   1.0000   0.0404
  -9.250  -0.9342   0.03124   0.02411  -0.0164   1.0000   0.0414
  -9.000  -0.9182   0.02799   0.02069  -0.0153   1.0000   0.0430
  -8.750  -0.8981   0.02652   0.01916  -0.0144   1.0000   0.0447
  -8.500  -0.8775   0.02539   0.01791  -0.0134   1.0000   0.0472
  -8.250  -0.8563   0.02437   0.01667  -0.0123   1.0000   0.0499
  -8.000  -0.8360   0.02250   0.01471  -0.0113   1.0000   0.0526
  -7.750  -0.8145   0.02143   0.01364  -0.0104   1.0000   0.0557
  -7.500  -0.7922   0.02062   0.01271  -0.0094   1.0000   0.0598
  -7.250  -0.7717   0.01932   0.01141  -0.0083   1.0000   0.0644
  -7.000  -0.7498   0.01853   0.01061  -0.0073   1.0000   0.0696
  -6.750  -0.7290   0.01754   0.00959  -0.0061   1.0000   0.0761
  -6.500  -0.7068   0.01689   0.00891  -0.0050   1.0000   0.0841
  -6.250  -0.6863   0.01601   0.00810  -0.0038   1.0000   0.0939
  -6.000  -0.6653   0.01526   0.00740  -0.0026   1.0000   0.1066
  -5.750  -0.6440   0.01457   0.00676  -0.0014   1.0000   0.1234
  -5.500  -0.6233   0.01386   0.00618  -0.0002   1.0000   0.1453
  -5.250  -0.6022   0.01322   0.00570   0.0009   1.0000   0.1736
  -5.000  -0.5811   0.01264   0.00529   0.0021   1.0000   0.2077
  -4.750  -0.5596   0.01214   0.00493   0.0032   1.0000   0.2454
  -4.500  -0.5382   0.01168   0.00465   0.0043   1.0000   0.2842
  -4.250  -0.5166   0.01129   0.00441   0.0055   1.0000   0.3232
  -4.000  -0.4950   0.01094   0.00421   0.0067   1.0000   0.3616
  -3.750  -0.4735   0.01063   0.00403   0.0079   1.0000   0.3990
  -3.500  -0.4521   0.01036   0.00390   0.0092   1.0000   0.4354
  -3.250  -0.4308   0.01012   0.00379   0.0105   1.0000   0.4711
  -3.000  -0.4098   0.00992   0.00370   0.0118   1.0000   0.5058
  -2.750  -0.3892   0.00973   0.00365   0.0133   1.0000   0.5393
  -2.500  -0.3690   0.00958   0.00363   0.0148   1.0000   0.5724
  -2.250  -0.3493   0.00947   0.00365   0.0163   1.0000   0.6054
  -2.000  -0.3303   0.00939   0.00370   0.0180   1.0000   0.6379
  -1.750  -0.2985   0.00934   0.00379   0.0170   0.9952   0.6746
  -1.500  -0.2536   0.00923   0.00385   0.0137   0.9850   0.7126
  -1.250  -0.2101   0.00911   0.00386   0.0107   0.9738   0.7496
  -0.750  -0.1229   0.00884   0.00385   0.0054   0.9520   0.8184
  -0.500  -0.0808   0.00873   0.00383   0.0033   0.9388   0.8494
  -0.250  -0.0412   0.00866   0.00383   0.0018   0.9214   0.8776
   0.000   0.0000   0.00864   0.00384   0.0000   0.9011   0.9010
   0.250   0.0412   0.00866   0.00383  -0.0018   0.8777   0.9213
   0.500   0.0808   0.00873   0.00384  -0.0033   0.8494   0.9389
   0.750   0.1229   0.00884   0.00385  -0.0054   0.8183   0.9519
   1.000   0.1672   0.00898   0.00386  -0.0081   0.7852   0.9625
   1.250   0.2101   0.00911   0.00386  -0.0108   0.7496   0.9738
   1.500   0.2536   0.00924   0.00385  -0.0137   0.7126   0.9849
   1.750   0.2984   0.00934   0.00379  -0.0170   0.6745   0.9952
   2.000   0.3304   0.00939   0.00370  -0.0180   0.6376   1.0000
   2.250   0.3495   0.00947   0.00365  -0.0164   0.6052   1.0000
   2.500   0.3692   0.00958   0.00363  -0.0148   0.5725   1.0000
   2.750   0.3894   0.00973   0.00365  -0.0133   0.5394   1.0000
   3.000   0.4100   0.00992   0.00370  -0.0119   0.5059   1.0000
   3.250   0.4310   0.01012   0.00379  -0.0105   0.4712   1.0000
   3.500   0.4523   0.01036   0.00390  -0.0092   0.4352   1.0000
   3.750   0.4736   0.01063   0.00403  -0.0079   0.3989   1.0000
   4.000   0.4952   0.01094   0.00421  -0.0067   0.3615   1.0000
   4.250   0.5168   0.01129   0.00441  -0.0055   0.3231   1.0000
   4.500   0.5384   0.01168   0.00465  -0.0044   0.2841   1.0000
   4.750   0.5598   0.01214   0.00493  -0.0032   0.2454   1.0000
   5.000   0.5813   0.01264   0.00529  -0.0021   0.2075   1.0000
   5.250   0.6024   0.01322   0.00570  -0.0010   0.1736   1.0000
   5.500   0.6234   0.01386   0.00619   0.0002   0.1452   1.0000
   5.750   0.6442   0.01457   0.00676   0.0014   0.1234   1.0000
   6.000   0.6654   0.01526   0.00740   0.0026   0.1065   1.0000
   6.250   0.6864   0.01600   0.00810   0.0038   0.0938   1.0000
   6.500   0.7068   0.01689   0.00891   0.0050   0.0841   1.0000
   6.750   0.7290   0.01753   0.00959   0.0061   0.0760   1.0000
   7.000   0.7497   0.01853   0.01061   0.0073   0.0696   1.0000
   7.250   0.7716   0.01933   0.01142   0.0083   0.0644   1.0000
   7.500   0.7921   0.02065   0.01274   0.0094   0.0599   1.0000
   7.750   0.8144   0.02145   0.01365   0.0104   0.0558   1.0000
   8.000   0.8358   0.02250   0.01471   0.0114   0.0526   1.0000
   8.250   0.8562   0.02436   0.01666   0.0124   0.0499   1.0000
   8.500   0.8774   0.02538   0.01790   0.0135   0.0472   1.0000
   8.750   0.8979   0.02655   0.01919   0.0145   0.0448   1.0000
   9.000   0.9180   0.02798   0.02068   0.0154   0.0430   1.0000
   9.250   0.9340   0.03127   0.02414   0.0164   0.0415   1.0000
   9.500   0.9494   0.03272   0.02598   0.0180   0.0403   1.0000
   9.750   0.9623   0.03477   0.02839   0.0196   0.0390   1.0000
  10.000   0.9734   0.03696   0.03088   0.0212   0.0377   1.0000
  10.250   0.9820   0.03941   0.03361   0.0227   0.0367   1.0000
  10.500   0.9851   0.04241   0.03692   0.0245   0.0364   1.0000
  10.750   0.9868   0.04522   0.03999   0.0262   0.0358   1.0000
  11.000   0.9761   0.04891   0.04400   0.0283   0.0358   1.0000
  11.250   0.9404   0.05370   0.04918   0.0313   0.0364   1.0000
  11.500   0.8979   0.06009   0.05590   0.0300   0.0375   1.0000
  11.750   0.8590   0.06816   0.06419   0.0244   0.0381   1.0000
  12.000   0.8112   0.08086   0.07707   0.0138   0.0393   1.0000
  12.250   0.7723   0.09445   0.09070   0.0045   0.0407   1.0000
  12.500   0.7612   0.10139   0.09761   0.0018   0.0414   1.0000
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