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RAE 100 AIRFOIL (rae100-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RAE 100 AIRFOIL (rae100-il)
Reynolds number: 100,000
Max Cl/Cd: 35.24 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae100-il-100000-n5.txt
Download as CSV file: xf-rae100-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.7911   0.09882   0.09340  -0.0011   1.0000   0.0333
 -12.500  -0.8322   0.08482   0.07932  -0.0107   1.0000   0.0328
 -12.250  -0.8675   0.07390   0.06826  -0.0191   1.0000   0.0323
 -12.000  -0.8957   0.06595   0.06013  -0.0251   1.0000   0.0321
 -11.750  -0.9205   0.05982   0.05378  -0.0288   1.0000   0.0320
 -11.500  -0.9406   0.05520   0.04892  -0.0301   1.0000   0.0320
 -11.250  -0.9584   0.05143   0.04488  -0.0294   1.0000   0.0322
 -11.000  -0.9716   0.04826   0.04142  -0.0274   1.0000   0.0326
 -10.750  -0.9770   0.04512   0.03790  -0.0256   1.0000   0.0330
 -10.500  -0.9771   0.04222   0.03459  -0.0239   1.0000   0.0339
 -10.250  -0.9661   0.04044   0.03278  -0.0228   1.0000   0.0351
 -10.000  -0.9545   0.03878   0.03100  -0.0217   1.0000   0.0364
  -9.750  -0.9424   0.03686   0.02885  -0.0204   1.0000   0.0379
  -9.500  -0.9287   0.03478   0.02646  -0.0191   1.0000   0.0395
  -9.250  -0.9129   0.03280   0.02413  -0.0178   1.0000   0.0411
  -9.000  -0.8962   0.03120   0.02247  -0.0168   1.0000   0.0431
  -8.750  -0.8781   0.02998   0.02119  -0.0159   1.0000   0.0455
  -8.500  -0.8591   0.02862   0.01964  -0.0148   1.0000   0.0484
  -8.250  -0.8395   0.02722   0.01804  -0.0137   1.0000   0.0511
  -8.000  -0.8207   0.02606   0.01690  -0.0127   1.0000   0.0544
  -7.750  -0.8005   0.02502   0.01574  -0.0117   1.0000   0.0587
  -7.500  -0.7807   0.02388   0.01452  -0.0105   1.0000   0.0628
  -7.250  -0.7605   0.02296   0.01357  -0.0095   1.0000   0.0682
  -7.000  -0.7400   0.02201   0.01256  -0.0084   1.0000   0.0745
  -6.750  -0.7193   0.02116   0.01167  -0.0074   1.0000   0.0821
  -6.500  -0.6987   0.02031   0.01083  -0.0063   1.0000   0.0911
  -6.250  -0.6777   0.01953   0.01005  -0.0052   1.0000   0.1023
  -6.000  -0.6565   0.01879   0.00934  -0.0042   1.0000   0.1163
  -5.750  -0.6352   0.01809   0.00868  -0.0032   1.0000   0.1335
  -5.500  -0.6135   0.01745   0.00809  -0.0022   1.0000   0.1550
  -5.250  -0.5922   0.01681   0.00757  -0.0012   1.0000   0.1803
  -5.000  -0.5707   0.01623   0.00711  -0.0002   1.0000   0.2089
  -4.750  -0.5491   0.01571   0.00669   0.0009   1.0000   0.2412
  -4.500  -0.5274   0.01523   0.00633   0.0019   1.0000   0.2749
  -4.250  -0.5059   0.01478   0.00602   0.0031   1.0000   0.3099
  -4.000  -0.4842   0.01438   0.00574   0.0042   1.0000   0.3455
  -3.750  -0.4625   0.01403   0.00550   0.0054   1.0000   0.3811
  -3.500  -0.4409   0.01370   0.00530   0.0066   1.0000   0.4160
  -3.250  -0.4193   0.01341   0.00514   0.0078   1.0000   0.4503
  -3.000  -0.3978   0.01315   0.00499   0.0091   1.0000   0.4843
  -2.750  -0.3764   0.01292   0.00487   0.0104   1.0000   0.5175
  -2.500  -0.3552   0.01272   0.00479   0.0118   1.0000   0.5500
  -2.250  -0.3343   0.01255   0.00474   0.0132   1.0000   0.5820
  -2.000  -0.3137   0.01241   0.00470   0.0147   1.0000   0.6136
  -1.750  -0.2795   0.01229   0.00472   0.0134   0.9908   0.6489
  -1.500  -0.2399   0.01219   0.00473   0.0112   0.9774   0.6850
  -1.250  -0.2002   0.01210   0.00474   0.0091   0.9634   0.7199
  -0.750  -0.1217   0.01193   0.00476   0.0055   0.9321   0.7859
  -0.500  -0.0820   0.01188   0.00478   0.0038   0.9139   0.8168
  -0.250  -0.0408   0.01184   0.00479   0.0018   0.8944   0.8453
   0.000   0.0000   0.01183   0.00481   0.0000   0.8709   0.8709
   0.250   0.0408   0.01184   0.00480  -0.0018   0.8453   0.8944
   0.500   0.0820   0.01188   0.00478  -0.0038   0.8168   0.9139
   0.750   0.1217   0.01193   0.00476  -0.0055   0.7860   0.9320
   1.250   0.2002   0.01210   0.00474  -0.0091   0.7200   0.9634
   1.500   0.2399   0.01219   0.00473  -0.0112   0.6849   0.9774
   1.750   0.2795   0.01229   0.00472  -0.0134   0.6490   0.9908
   2.000   0.3138   0.01241   0.00470  -0.0147   0.6137   1.0000
   2.250   0.3344   0.01255   0.00472  -0.0132   0.5820   1.0000
   2.500   0.3554   0.01272   0.00479  -0.0118   0.5500   1.0000
   2.750   0.3765   0.01292   0.00487  -0.0105   0.5174   1.0000
   3.000   0.3979   0.01315   0.00499  -0.0092   0.4843   1.0000
   3.250   0.4194   0.01341   0.00514  -0.0079   0.4503   1.0000
   3.500   0.4410   0.01370   0.00530  -0.0066   0.4158   1.0000
   3.750   0.4626   0.01403   0.00550  -0.0054   0.3811   1.0000
   4.000   0.4844   0.01438   0.00574  -0.0042   0.3455   1.0000
   4.250   0.5060   0.01478   0.00602  -0.0031   0.3098   1.0000
   4.500   0.5275   0.01523   0.00633  -0.0020   0.2750   1.0000
   4.750   0.5492   0.01571   0.00669  -0.0009   0.2412   1.0000
   5.000   0.5708   0.01623   0.00711   0.0001   0.2090   1.0000
   5.250   0.5923   0.01681   0.00757   0.0012   0.1802   1.0000
   5.500   0.6136   0.01745   0.00809   0.0022   0.1549   1.0000
   5.750   0.6353   0.01809   0.00868   0.0032   0.1336   1.0000
   6.000   0.6565   0.01879   0.00934   0.0042   0.1162   1.0000
   6.250   0.6777   0.01953   0.01005   0.0052   0.1023   1.0000
   6.500   0.6987   0.02031   0.01083   0.0063   0.0911   1.0000
   6.750   0.7193   0.02116   0.01167   0.0074   0.0820   1.0000
   7.000   0.7399   0.02201   0.01256   0.0084   0.0745   1.0000
   7.250   0.7604   0.02296   0.01357   0.0095   0.0682   1.0000
   7.500   0.7806   0.02388   0.01451   0.0105   0.0628   1.0000
   7.750   0.8004   0.02502   0.01573   0.0117   0.0587   1.0000
   8.000   0.8206   0.02605   0.01690   0.0127   0.0543   1.0000
   8.250   0.8393   0.02721   0.01803   0.0137   0.0510   1.0000
   8.500   0.8589   0.02862   0.01964   0.0148   0.0484   1.0000
   8.750   0.8779   0.02999   0.02120   0.0159   0.0457   1.0000
   9.000   0.8959   0.03120   0.02248   0.0169   0.0431   1.0000
   9.250   0.9127   0.03280   0.02412   0.0179   0.0412   1.0000
   9.500   0.9285   0.03477   0.02644   0.0192   0.0396   1.0000
   9.750   0.9421   0.03687   0.02885   0.0205   0.0380   1.0000
  10.000   0.9542   0.03880   0.03102   0.0217   0.0365   1.0000
  10.250   0.9660   0.04039   0.03273   0.0229   0.0350   1.0000
  10.500   0.9766   0.04223   0.03462   0.0240   0.0340   1.0000
  10.750   0.9771   0.04508   0.03785   0.0256   0.0331   1.0000
  11.000   0.9713   0.04826   0.04141   0.0274   0.0325   1.0000
  11.250   0.9587   0.05139   0.04484   0.0295   0.0323   1.0000
  11.500   0.9416   0.05509   0.04880   0.0301   0.0321   1.0000
  11.750   0.9205   0.05980   0.05376   0.0288   0.0320   1.0000
  12.000   0.8961   0.06589   0.06008   0.0251   0.0321   1.0000
  12.250   0.8690   0.07366   0.06801   0.0193   0.0324   1.0000
  12.500   0.8351   0.08426   0.07876   0.0112   0.0328   1.0000
  12.750   0.7937   0.09825   0.09283   0.0015   0.0333   1.0000
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