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RAE 103 AIRFOIL (rae103-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: RAE 103 AIRFOIL (rae103-il)
Reynolds number: 500,000
Max Cl/Cd: 52.56 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae103-il-500000-n5.txt
Download as CSV file: xf-rae103-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.8669   0.07270   0.07025  -0.0233   1.0000   0.0060
 -13.000  -0.8990   0.06169   0.05904  -0.0315   1.0000   0.0059
 -12.750  -0.9282   0.05386   0.05099  -0.0360   1.0000   0.0059
 -12.500  -0.9464   0.04878   0.04571  -0.0379   1.0000   0.0059
 -12.250  -0.9730   0.04340   0.04006  -0.0382   1.0000   0.0059
 -12.000  -0.9836   0.04031   0.03676  -0.0373   1.0000   0.0060
 -11.750  -0.9973   0.03717   0.03337  -0.0351   1.0000   0.0060
 -11.500  -1.0061   0.03465   0.03061  -0.0322   1.0000   0.0061
 -11.250  -1.0109   0.03259   0.02833  -0.0288   1.0000   0.0062
 -11.000  -1.0120   0.03065   0.02615  -0.0255   1.0000   0.0064
 -10.750  -1.0069   0.02877   0.02401  -0.0230   1.0000   0.0065
 -10.500  -0.9978   0.02716   0.02218  -0.0208   1.0000   0.0066
 -10.250  -0.9842   0.02602   0.02085  -0.0192   1.0000   0.0068
 -10.000  -0.9752   0.02414   0.01875  -0.0169   1.0000   0.0071
  -9.750  -0.9610   0.02291   0.01739  -0.0152   1.0000   0.0073
  -9.500  -0.9439   0.02210   0.01649  -0.0139   1.0000   0.0076
  -9.250  -0.9267   0.02121   0.01547  -0.0125   1.0000   0.0079
  -9.000  -0.9091   0.02032   0.01448  -0.0110   1.0000   0.0082
  -8.750  -0.8912   0.01947   0.01352  -0.0096   1.0000   0.0085
  -8.500  -0.8735   0.01859   0.01253  -0.0080   1.0000   0.0088
  -8.250  -0.8552   0.01783   0.01166  -0.0065   1.0000   0.0092
  -8.000  -0.8370   0.01709   0.01082  -0.0050   1.0000   0.0096
  -7.750  -0.8180   0.01647   0.01010  -0.0035   1.0000   0.0099
  -7.500  -0.8012   0.01563   0.00917  -0.0017   1.0000   0.0104
  -7.250  -0.7831   0.01499   0.00849   0.0000   1.0000   0.0110
  -7.000  -0.7636   0.01454   0.00800   0.0014   1.0000   0.0118
  -6.750  -0.7418   0.01411   0.00754   0.0023   0.9995   0.0128
  -6.500  -0.7101   0.01363   0.00699   0.0011   0.9949   0.0140
  -6.250  -0.6807   0.01303   0.00634   0.0004   0.9892   0.0151
  -6.000  -0.6496   0.01250   0.00577  -0.0007   0.9839   0.0170
  -5.750  -0.6190   0.01210   0.00533  -0.0016   0.9772   0.0189
  -5.500  -0.5858   0.01170   0.00489  -0.0031   0.9713   0.0217
  -5.250  -0.5543   0.01128   0.00448  -0.0041   0.9629   0.0257
  -5.000  -0.5204   0.01094   0.00409  -0.0057   0.9552   0.0300
  -4.750  -0.4883   0.01058   0.00375  -0.0068   0.9444   0.0379
  -4.500  -0.4566   0.01025   0.00343  -0.0078   0.9321   0.0495
  -4.250  -0.4267   0.00992   0.00313  -0.0085   0.9175   0.0663
  -4.000  -0.3995   0.00956   0.00285  -0.0085   0.9013   0.0944
  -3.750  -0.3743   0.00920   0.00259  -0.0082   0.8849   0.1331
  -3.250  -0.3285   0.00827   0.00208  -0.0067   0.8550   0.2676
  -3.000  -0.3071   0.00771   0.00183  -0.0057   0.8415   0.3614
  -2.750  -0.2868   0.00712   0.00162  -0.0044   0.8288   0.4704
  -2.500  -0.2643   0.00680   0.00155  -0.0034   0.8170   0.5523
  -2.250  -0.2393   0.00669   0.00149  -0.0028   0.8062   0.5891
  -2.000  -0.2136   0.00662   0.00143  -0.0023   0.7962   0.6160
  -1.750  -0.1874   0.00657   0.00139  -0.0019   0.7868   0.6377
  -1.500  -0.1610   0.00653   0.00136  -0.0015   0.7784   0.6558
  -1.250  -0.1345   0.00650   0.00133  -0.0012   0.7700   0.6715
  -1.000  -0.1078   0.00648   0.00131  -0.0009   0.7617   0.6858
  -0.750  -0.0810   0.00647   0.00129  -0.0006   0.7539   0.6986
  -0.500  -0.0540   0.00645   0.00128  -0.0004   0.7458   0.7101
  -0.250  -0.0271   0.00644   0.00128  -0.0002   0.7379   0.7201
   0.000   0.0000   0.00644   0.00127   0.0000   0.7292   0.7292
   0.250   0.0271   0.00644   0.00128   0.0002   0.7202   0.7379
   0.500   0.0540   0.00645   0.00128   0.0004   0.7101   0.7457
   0.750   0.0810   0.00647   0.00129   0.0006   0.6985   0.7540
   1.000   0.1078   0.00648   0.00131   0.0009   0.6858   0.7617
   1.250   0.1345   0.00650   0.00133   0.0012   0.6717   0.7701
   1.500   0.1610   0.00653   0.00136   0.0015   0.6558   0.7784
   1.750   0.1874   0.00657   0.00139   0.0019   0.6375   0.7869
   2.000   0.2136   0.00662   0.00143   0.0023   0.6160   0.7962
   2.250   0.2393   0.00669   0.00148   0.0028   0.5896   0.8062
   2.500   0.2643   0.00681   0.00155   0.0034   0.5519   0.8170
   2.750   0.2870   0.00711   0.00162   0.0044   0.4720   0.8287
   3.000   0.3072   0.00771   0.00183   0.0057   0.3626   0.8415
   3.250   0.3286   0.00828   0.00208   0.0067   0.2674   0.8550
   3.750   0.3743   0.00921   0.00260   0.0082   0.1326   0.8850
   4.000   0.3996   0.00956   0.00285   0.0085   0.0950   0.9013
   4.250   0.4268   0.00991   0.00313   0.0085   0.0673   0.9176
   4.500   0.4566   0.01025   0.00343   0.0079   0.0494   0.9322
   4.750   0.4883   0.01059   0.00375   0.0068   0.0378   0.9444
   5.000   0.5203   0.01094   0.00409   0.0057   0.0299   0.9552
   5.250   0.5543   0.01128   0.00448   0.0041   0.0257   0.9630
   5.500   0.5858   0.01169   0.00489   0.0031   0.0217   0.9713
   5.750   0.6189   0.01210   0.00534   0.0016   0.0190   0.9773
   6.000   0.6495   0.01250   0.00577   0.0008   0.0170   0.9839
   6.250   0.6807   0.01302   0.00633  -0.0003   0.0152   0.9892
   6.500   0.7100   0.01365   0.00702  -0.0010   0.0140   0.9949
   6.750   0.7416   0.01413   0.00756  -0.0022   0.0129   0.9994
   7.000   0.7637   0.01453   0.00800  -0.0014   0.0118   1.0000
   7.250   0.7830   0.01500   0.00850   0.0001   0.0112   1.0000
   7.500   0.8014   0.01561   0.00915   0.0016   0.0105   1.0000
   7.750   0.8182   0.01644   0.01008   0.0035   0.0099   1.0000
   8.000   0.8366   0.01713   0.01086   0.0050   0.0096   1.0000
   8.250   0.8552   0.01783   0.01166   0.0065   0.0093   1.0000
   8.500   0.8732   0.01862   0.01256   0.0081   0.0089   1.0000
   8.750   0.8912   0.01947   0.01352   0.0096   0.0085   1.0000
   9.000   0.9088   0.02036   0.01453   0.0111   0.0082   1.0000
   9.250   0.9265   0.02122   0.01549   0.0125   0.0079   1.0000
   9.500   0.9443   0.02202   0.01640   0.0138   0.0076   1.0000
   9.750   0.9612   0.02285   0.01731   0.0152   0.0073   1.0000
  10.000   0.9751   0.02410   0.01871   0.0169   0.0070   1.0000
  10.250   0.9860   0.02572   0.02052   0.0189   0.0067   1.0000
  10.500   0.9984   0.02708   0.02209   0.0208   0.0066   1.0000
  10.750   1.0077   0.02866   0.02389   0.0229   0.0065   1.0000
  11.000   1.0137   0.03044   0.02592   0.0253   0.0063   1.0000
  11.250   1.0116   0.03252   0.02825   0.0287   0.0063   1.0000
  11.500   1.0071   0.03458   0.03053   0.0320   0.0061   1.0000
  11.750   0.9977   0.03715   0.03335   0.0350   0.0061   1.0000
  12.000   0.9859   0.04011   0.03655   0.0371   0.0060   1.0000
  12.250   0.9710   0.04368   0.04035   0.0382   0.0059   1.0000
  12.500   0.9484   0.04860   0.04553   0.0378   0.0059   1.0000
  12.750   0.9310   0.05358   0.05070   0.0360   0.0059   1.0000
  13.000   0.9022   0.06128   0.05863   0.0316   0.0059   1.0000
  13.250   0.8706   0.07200   0.06955   0.0237   0.0061   1.0000
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