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RAE 102 AIRFOIL (rae102-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RAE 102 AIRFOIL (rae102-il)
Reynolds number: 500,000
Max Cl/Cd: 57.25 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae102-il-500000.txt
Download as CSV file: xf-rae102-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7060   0.08600   0.08370  -0.0136   1.0000   0.0176
 -11.250  -0.7369   0.07371   0.07133  -0.0231   1.0000   0.0172
 -11.000  -0.8699   0.05031   0.04717  -0.0345   1.0000   0.0132
 -10.750  -0.8874   0.04715   0.04383  -0.0326   1.0000   0.0132
 -10.500  -0.8952   0.04523   0.04175  -0.0297   1.0000   0.0131
 -10.250  -0.9038   0.04256   0.03887  -0.0267   1.0000   0.0131
 -10.000  -0.9103   0.03928   0.03531  -0.0240   1.0000   0.0131
  -9.750  -0.9200   0.03466   0.03029  -0.0208   1.0000   0.0132
  -9.500  -0.9202   0.03071   0.02597  -0.0181   1.0000   0.0135
  -9.250  -0.9103   0.02820   0.02321  -0.0161   1.0000   0.0137
  -9.000  -0.8966   0.02626   0.02108  -0.0145   1.0000   0.0141
  -8.750  -0.8809   0.02451   0.01913  -0.0130   1.0000   0.0144
  -8.500  -0.8634   0.02308   0.01754  -0.0115   1.0000   0.0148
  -8.250  -0.8449   0.02177   0.01608  -0.0102   1.0000   0.0154
  -8.000  -0.8257   0.02054   0.01470  -0.0089   1.0000   0.0160
  -7.750  -0.8061   0.01935   0.01338  -0.0075   1.0000   0.0166
  -7.500  -0.7860   0.01841   0.01232  -0.0062   1.0000   0.0174
  -7.250  -0.7647   0.01781   0.01161  -0.0050   1.0000   0.0180
  -7.000  -0.7503   0.01595   0.00964  -0.0028   1.0000   0.0194
  -6.750  -0.7305   0.01530   0.00897  -0.0015   1.0000   0.0208
  -6.500  -0.7105   0.01468   0.00831  -0.0001   1.0000   0.0222
  -6.250  -0.6905   0.01408   0.00765   0.0014   1.0000   0.0237
  -6.000  -0.6695   0.01367   0.00718   0.0027   1.0000   0.0249
  -5.750  -0.6544   0.01260   0.00606   0.0049   1.0000   0.0279
  -5.500  -0.6340   0.01222   0.00567   0.0063   1.0000   0.0311
  -5.250  -0.6134   0.01190   0.00530   0.0077   1.0000   0.0337
  -5.000  -0.5961   0.01122   0.00463   0.0096   1.0000   0.0398
  -4.750  -0.5765   0.01090   0.00427   0.0111   1.0000   0.0461
  -4.500  -0.5479   0.01038   0.00382   0.0106   0.9981   0.0623
  -4.250  -0.5114   0.00977   0.00343   0.0083   0.9940   0.1043
  -4.000  -0.4781   0.00897   0.00304   0.0065   0.9885   0.1917
  -3.750  -0.4445   0.00796   0.00263   0.0044   0.9837   0.3326
  -3.500  -0.4138   0.00723   0.00243   0.0033   0.9762   0.4637
  -3.250  -0.3766   0.00695   0.00231   0.0012   0.9713   0.5202
  -3.000  -0.3425   0.00675   0.00220  -0.0002   0.9631   0.5542
  -2.750  -0.3059   0.00660   0.00208  -0.0020   0.9560   0.5824
  -2.500  -0.2731   0.00647   0.00199  -0.0030   0.9440   0.6049
  -2.250  -0.2410   0.00636   0.00190  -0.0037   0.9303   0.6254
  -2.000  -0.2108   0.00627   0.00181  -0.0040   0.9140   0.6443
  -1.750  -0.1828   0.00622   0.00174  -0.0038   0.8960   0.6622
  -1.500  -0.1562   0.00618   0.00169  -0.0034   0.8769   0.6795
  -1.250  -0.1300   0.00615   0.00164  -0.0028   0.8582   0.6959
  -1.000  -0.1041   0.00614   0.00160  -0.0022   0.8402   0.7121
  -0.750  -0.0782   0.00612   0.00158  -0.0016   0.8224   0.7279
  -0.500  -0.0522   0.00611   0.00156  -0.0011   0.8056   0.7434
  -0.250  -0.0261   0.00611   0.00155  -0.0005   0.7897   0.7587
   0.000   0.0000   0.00611   0.00155   0.0000   0.7741   0.7741
   0.250   0.0261   0.00611   0.00155   0.0005   0.7587   0.7897
   0.500   0.0522   0.00611   0.00156   0.0010   0.7434   0.8056
   0.750   0.0782   0.00612   0.00158   0.0016   0.7278   0.8224
   1.000   0.1041   0.00614   0.00160   0.0022   0.7121   0.8402
   1.250   0.1300   0.00615   0.00164   0.0028   0.6959   0.8582
   1.500   0.1562   0.00618   0.00169   0.0034   0.6795   0.8769
   1.750   0.1829   0.00622   0.00174   0.0038   0.6622   0.8960
   2.000   0.2108   0.00627   0.00181   0.0040   0.6440   0.9141
   2.250   0.2410   0.00636   0.00190   0.0037   0.6252   0.9303
   2.500   0.2731   0.00647   0.00199   0.0030   0.6052   0.9441
   2.750   0.3059   0.00660   0.00208   0.0020   0.5821   0.9561
   3.000   0.3425   0.00675   0.00220   0.0002   0.5548   0.9632
   3.250   0.3767   0.00695   0.00230  -0.0012   0.5193   0.9714
   3.500   0.4139   0.00723   0.00242  -0.0033   0.4645   0.9764
   3.750   0.4446   0.00796   0.00263  -0.0044   0.3308   0.9838
   4.000   0.4782   0.00896   0.00303  -0.0065   0.1921   0.9886
   4.250   0.5114   0.00977   0.00343  -0.0083   0.1038   0.9941
   4.500   0.5482   0.01038   0.00382  -0.0107   0.0622   0.9982
   4.750   0.5759   0.01088   0.00426  -0.0110   0.0466   1.0000
   5.000   0.5955   0.01122   0.00462  -0.0095   0.0398   1.0000
   5.250   0.6128   0.01188   0.00529  -0.0076   0.0337   1.0000
   5.500   0.6335   0.01221   0.00566  -0.0062   0.0311   1.0000
   5.750   0.6538   0.01261   0.00607  -0.0048   0.0280   1.0000
   6.000   0.6690   0.01367   0.00718  -0.0026   0.0249   1.0000
   6.250   0.6901   0.01408   0.00766  -0.0013   0.0237   1.0000
   6.500   0.7101   0.01468   0.00831   0.0002   0.0222   1.0000
   6.750   0.7304   0.01527   0.00894   0.0015   0.0207   1.0000
   7.000   0.7500   0.01597   0.00965   0.0029   0.0194   1.0000
   7.250   0.7646   0.01779   0.01159   0.0050   0.0180   1.0000
   7.500   0.7860   0.01839   0.01230   0.0062   0.0173   1.0000
   7.750   0.8061   0.01939   0.01342   0.0075   0.0166   1.0000
   8.000   0.8258   0.02055   0.01472   0.0088   0.0160   1.0000
   8.250   0.8451   0.02179   0.01610   0.0102   0.0154   1.0000
   8.500   0.8637   0.02314   0.01760   0.0115   0.0149   1.0000
   8.750   0.8814   0.02447   0.01908   0.0129   0.0144   1.0000
   9.000   0.8971   0.02628   0.02111   0.0144   0.0141   1.0000
   9.250   0.9106   0.02832   0.02336   0.0161   0.0138   1.0000
   9.500   0.9190   0.03110   0.02638   0.0181   0.0134   1.0000
   9.750   0.9219   0.03446   0.03007   0.0205   0.0133   1.0000
  10.000   0.9104   0.03939   0.03543   0.0238   0.0131   1.0000
  10.250   0.9057   0.04247   0.03877   0.0264   0.0131   1.0000
  10.500   0.8989   0.04502   0.04153   0.0293   0.0131   1.0000
  10.750   0.8826   0.04778   0.04447   0.0326   0.0131   1.0000
  11.000   0.8737   0.05008   0.04693   0.0343   0.0133   1.0000
  11.250   0.8496   0.05453   0.05157   0.0341   0.0132   1.0000
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