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RAE 102 AIRFOIL (rae102-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: RAE 102 AIRFOIL (rae102-il)
Reynolds number: 500,000
Max Cl/Cd: 54.7 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae102-il-500000-n5.txt
Download as CSV file: xf-rae102-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 102 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
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.9098   0.08572   0.08312  -0.0101   1.0000   0.0063
 -14.000  -0.9411   0.07383   0.07108  -0.0179   1.0000   0.0061
 -13.750  -0.9696   0.06399   0.06104  -0.0247   1.0000   0.0062
 -13.500  -0.9887   0.05711   0.05399  -0.0291   1.0000   0.0062
 -13.250  -1.0106   0.05065   0.04731  -0.0326   1.0000   0.0061
 -13.000  -1.0257   0.04584   0.04230  -0.0344   1.0000   0.0061
 -12.750  -1.0366   0.04204   0.03829  -0.0351   1.0000   0.0062
 -12.500  -1.0439   0.03902   0.03508  -0.0348   1.0000   0.0062
 -12.250  -1.0504   0.03638   0.03223  -0.0337   1.0000   0.0063
 -12.000  -1.0609   0.03362   0.02925  -0.0314   1.0000   0.0064
 -11.750  -1.0645   0.03159   0.02702  -0.0287   1.0000   0.0064
 -11.500  -1.0660   0.02991   0.02520  -0.0256   1.0000   0.0066
 -11.250  -1.0578   0.02891   0.02410  -0.0235   1.0000   0.0068
 -11.000  -1.0474   0.02772   0.02280  -0.0217   1.0000   0.0070
 -10.750  -1.0334   0.02683   0.02181  -0.0202   1.0000   0.0072
 -10.500  -1.0202   0.02563   0.02045  -0.0186   1.0000   0.0075
 -10.250  -1.0056   0.02450   0.01917  -0.0171   1.0000   0.0077
 -10.000  -0.9908   0.02324   0.01775  -0.0155   1.0000   0.0079
  -9.750  -0.9744   0.02216   0.01651  -0.0141   1.0000   0.0082
  -9.500  -0.9570   0.02118   0.01539  -0.0127   1.0000   0.0086
  -9.250  -0.9394   0.02018   0.01426  -0.0113   1.0000   0.0088
  -9.000  -0.9205   0.01936   0.01331  -0.0101   1.0000   0.0090
  -8.750  -0.9026   0.01842   0.01227  -0.0087   1.0000   0.0093
  -8.500  -0.8852   0.01747   0.01122  -0.0072   1.0000   0.0098
  -8.250  -0.8652   0.01683   0.01053  -0.0060   1.0000   0.0103
  -8.000  -0.8449   0.01625   0.00990  -0.0049   1.0000   0.0108
  -7.750  -0.8243   0.01571   0.00930  -0.0037   1.0000   0.0114
  -7.500  -0.8033   0.01523   0.00876  -0.0026   1.0000   0.0123
  -7.250  -0.7820   0.01480   0.00826  -0.0015   1.0000   0.0129
  -7.000  -0.7632   0.01409   0.00748   0.0000   1.0000   0.0138
  -6.750  -0.7425   0.01360   0.00697   0.0012   1.0000   0.0149
  -6.500  -0.7214   0.01318   0.00652   0.0024   1.0000   0.0160
  -6.250  -0.7002   0.01280   0.00608   0.0036   1.0000   0.0172
  -6.000  -0.6791   0.01243   0.00567   0.0048   1.0000   0.0186
  -5.750  -0.6470   0.01194   0.00518   0.0036   0.9959   0.0215
  -5.500  -0.6152   0.01159   0.00479   0.0025   0.9904   0.0242
  -5.250  -0.5828   0.01119   0.00438   0.0013   0.9845   0.0282
  -5.000  -0.5512   0.01087   0.00406   0.0003   0.9778   0.0335
  -4.750  -0.5175   0.01051   0.00372  -0.0012   0.9713   0.0425
  -4.500  -0.4851   0.01017   0.00342  -0.0024   0.9622   0.0543
  -4.250  -0.4515   0.00979   0.00312  -0.0039   0.9523   0.0751
  -4.000  -0.4183   0.00939   0.00283  -0.0053   0.9398   0.1069
  -3.750  -0.3875   0.00893   0.00254  -0.0062   0.9239   0.1542
  -3.500  -0.3597   0.00844   0.00226  -0.0065   0.9044   0.2169
  -3.000  -0.3124   0.00737   0.00176  -0.0052   0.8625   0.3937
  -2.750  -0.2883   0.00709   0.00164  -0.0045   0.8435   0.4619
  -2.500  -0.2631   0.00696   0.00155  -0.0039   0.8256   0.4978
  -2.250  -0.2376   0.00687   0.00148  -0.0034   0.8082   0.5272
  -2.000  -0.2117   0.00681   0.00140  -0.0029   0.7915   0.5517
  -1.750  -0.1858   0.00675   0.00135  -0.0024   0.7762   0.5739
  -1.500  -0.1595   0.00671   0.00131  -0.0020   0.7622   0.5941
  -1.250  -0.1333   0.00666   0.00127  -0.0016   0.7488   0.6128
  -1.000  -0.1069   0.00663   0.00124  -0.0012   0.7358   0.6304
  -0.750  -0.0804   0.00661   0.00121  -0.0009   0.7229   0.6466
  -0.500  -0.0537   0.00659   0.00120  -0.0005   0.7105   0.6613
  -0.250  -0.0269   0.00658   0.00119  -0.0003   0.6989   0.6745
   0.000   0.0000   0.00657   0.00119   0.0000   0.6870   0.6870
   0.250   0.0269   0.00658   0.00119   0.0003   0.6745   0.6989
   0.500   0.0537   0.00659   0.00120   0.0005   0.6613   0.7105
   0.750   0.0804   0.00661   0.00121   0.0009   0.6465   0.7228
   1.000   0.1069   0.00663   0.00124   0.0012   0.6305   0.7357
   1.250   0.1333   0.00666   0.00127   0.0016   0.6128   0.7489
   1.500   0.1595   0.00671   0.00131   0.0020   0.5941   0.7622
   1.750   0.1858   0.00675   0.00135   0.0024   0.5739   0.7762
   2.000   0.2117   0.00681   0.00140   0.0029   0.5513   0.7915
   2.250   0.2376   0.00687   0.00148   0.0034   0.5268   0.8082
   2.500   0.2632   0.00696   0.00155   0.0039   0.4984   0.8256
   2.750   0.2884   0.00709   0.00164   0.0045   0.4613   0.8435
   3.000   0.3126   0.00736   0.00176   0.0052   0.3958   0.8625
   3.250   0.3351   0.00791   0.00199   0.0061   0.2984   0.8835
   3.500   0.3598   0.00844   0.00226   0.0064   0.2174   0.9044
   3.750   0.3876   0.00893   0.00254   0.0062   0.1539   0.9239
   4.000   0.4183   0.00940   0.00283   0.0053   0.1058   0.9399
   4.250   0.4515   0.00980   0.00312   0.0039   0.0749   0.9523
   4.500   0.4853   0.01017   0.00342   0.0024   0.0543   0.9625
   4.750   0.5176   0.01051   0.00372   0.0012   0.0425   0.9714
   5.000   0.5513   0.01087   0.00406  -0.0003   0.0335   0.9781
   5.250   0.5831   0.01119   0.00438  -0.0013   0.0282   0.9848
   5.500   0.6155   0.01159   0.00479  -0.0025   0.0242   0.9905
   5.750   0.6472   0.01195   0.00519  -0.0036   0.0215   0.9961
   6.000   0.6786   0.01242   0.00567  -0.0047   0.0186   1.0000
   6.250   0.6997   0.01280   0.00608  -0.0035   0.0172   1.0000
   6.500   0.7210   0.01318   0.00651  -0.0023   0.0160   1.0000
   6.750   0.7422   0.01359   0.00696  -0.0012   0.0148   1.0000
   7.000   0.7628   0.01409   0.00748   0.0001   0.0138   1.0000
   7.250   0.7818   0.01479   0.00825   0.0015   0.0129   1.0000
   7.500   0.8031   0.01524   0.00876   0.0026   0.0123   1.0000
   7.750   0.8241   0.01573   0.00932   0.0038   0.0115   1.0000
   8.000   0.8449   0.01626   0.00990   0.0049   0.0108   1.0000
   8.250   0.8654   0.01683   0.01053   0.0060   0.0103   1.0000
   8.500   0.8853   0.01748   0.01123   0.0072   0.0099   1.0000
   8.750   0.9032   0.01839   0.01223   0.0086   0.0093   1.0000
   9.000   0.9209   0.01937   0.01332   0.0100   0.0091   1.0000
   9.250   0.9398   0.02020   0.01427   0.0113   0.0088   1.0000
   9.500   0.9581   0.02110   0.01531   0.0125   0.0085   1.0000
   9.750   0.9748   0.02222   0.01658   0.0140   0.0083   1.0000
  10.000   0.9910   0.02334   0.01786   0.0154   0.0080   1.0000
  10.250   1.0064   0.02451   0.01918   0.0169   0.0078   1.0000
  10.500   1.0207   0.02572   0.02057   0.0185   0.0075   1.0000
  10.750   1.0352   0.02672   0.02169   0.0199   0.0072   1.0000
  11.000   1.0475   0.02787   0.02297   0.0216   0.0070   1.0000
  11.250   1.0613   0.02864   0.02380   0.0230   0.0068   1.0000
  11.500   1.0670   0.03003   0.02534   0.0254   0.0067   1.0000
  11.750   1.0660   0.03165   0.02710   0.0284   0.0065   1.0000
  12.000   1.0597   0.03387   0.02952   0.0313   0.0064   1.0000
  12.250   1.0533   0.03627   0.03211   0.0333   0.0063   1.0000
  12.500   1.0469   0.03891   0.03496   0.0345   0.0062   1.0000
  12.750   1.0393   0.04195   0.03819   0.0348   0.0062   1.0000
  13.000   1.0261   0.04604   0.04251   0.0341   0.0061   1.0000
  13.250   1.0099   0.05100   0.04766   0.0321   0.0062   1.0000
  13.500   0.9920   0.05696   0.05383   0.0288   0.0061   1.0000
  13.750   0.9727   0.06386   0.06092   0.0244   0.0061   1.0000
  14.000   0.9429   0.07389   0.07113   0.0175   0.0062   1.0000
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