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RAE 102 AIRFOIL (rae102-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: RAE 102 AIRFOIL (rae102-il)
Reynolds number: 1,000,000
Max Cl/Cd: 65.59 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae102-il-1000000.txt
Download as CSV file: xf-rae102-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.9800   0.06146   0.05923  -0.0266   1.0000   0.0067
 -13.500  -0.9898   0.05627   0.05394  -0.0301   1.0000   0.0068
 -13.250  -1.0238   0.04798   0.04533  -0.0345   1.0000   0.0066
 -13.000  -1.0398   0.04326   0.04043  -0.0362   1.0000   0.0066
 -12.750  -1.0535   0.03942   0.03641  -0.0365   1.0000   0.0067
 -12.500  -1.0592   0.03694   0.03381  -0.0358   1.0000   0.0068
 -12.250  -1.0655   0.03463   0.03137  -0.0342   1.0000   0.0069
 -12.000  -1.0650   0.03321   0.02986  -0.0323   1.0000   0.0070
 -11.750  -1.0788   0.03046   0.02684  -0.0281   1.0000   0.0069
 -11.500  -1.0757   0.02929   0.02557  -0.0252   1.0000   0.0071
 -11.250  -1.0649   0.02835   0.02455  -0.0234   1.0000   0.0072
 -11.000  -1.0575   0.02670   0.02272  -0.0212   1.0000   0.0073
 -10.750  -1.0449   0.02554   0.02144  -0.0195   1.0000   0.0075
 -10.500  -1.0334   0.02400   0.01972  -0.0176   1.0000   0.0077
 -10.250  -1.0189   0.02277   0.01834  -0.0160   1.0000   0.0078
 -10.000  -1.0036   0.02154   0.01696  -0.0144   1.0000   0.0080
  -9.750  -0.9867   0.02049   0.01578  -0.0129   1.0000   0.0082
  -9.500  -0.9686   0.01958   0.01475  -0.0116   1.0000   0.0086
  -9.250  -0.9501   0.01868   0.01374  -0.0102   1.0000   0.0088
  -9.000  -0.9284   0.01829   0.01329  -0.0093   1.0000   0.0091
  -8.750  -0.9144   0.01672   0.01154  -0.0072   1.0000   0.0095
  -8.500  -0.8992   0.01547   0.01018  -0.0053   1.0000   0.0100
  -8.250  -0.8793   0.01486   0.00952  -0.0040   1.0000   0.0105
  -8.000  -0.8586   0.01435   0.00897  -0.0028   1.0000   0.0109
  -7.750  -0.8380   0.01382   0.00840  -0.0016   1.0000   0.0114
  -7.500  -0.8171   0.01334   0.00787  -0.0004   1.0000   0.0121
  -7.250  -0.7959   0.01293   0.00741   0.0008   1.0000   0.0126
  -7.000  -0.7743   0.01257   0.00700   0.0020   1.0000   0.0129
  -6.750  -0.7584   0.01162   0.00595   0.0041   1.0000   0.0143
  -6.500  -0.7375   0.01125   0.00557   0.0054   1.0000   0.0154
  -6.250  -0.7163   0.01095   0.00527   0.0066   1.0000   0.0166
  -6.000  -0.6949   0.01071   0.00501   0.0078   1.0000   0.0177
  -5.750  -0.6666   0.01016   0.00438   0.0075   0.9987   0.0200
  -5.500  -0.6319   0.00980   0.00404   0.0058   0.9963   0.0230
  -5.250  -0.5969   0.00953   0.00375   0.0041   0.9936   0.0255
  -5.000  -0.5644   0.00912   0.00337   0.0029   0.9897   0.0324
  -4.750  -0.5300   0.00878   0.00305   0.0013   0.9859   0.0415
  -4.500  -0.4949   0.00845   0.00278  -0.0005   0.9828   0.0563
  -4.250  -0.4638   0.00806   0.00252  -0.0014   0.9759   0.0834
  -4.000  -0.4291   0.00760   0.00225  -0.0032   0.9706   0.1285
  -3.750  -0.3986   0.00705   0.00198  -0.0041   0.9605   0.1974
  -3.500  -0.3684   0.00642   0.00171  -0.0050   0.9478   0.2904
  -3.250  -0.3421   0.00576   0.00146  -0.0051   0.9301   0.4043
  -3.000  -0.3160   0.00549   0.00133  -0.0047   0.9099   0.4671
  -2.750  -0.2902   0.00536   0.00124  -0.0042   0.8885   0.5028
  -2.500  -0.2644   0.00529   0.00117  -0.0037   0.8682   0.5280
  -2.250  -0.2383   0.00525   0.00111  -0.0032   0.8483   0.5492
  -2.000  -0.2123   0.00521   0.00105  -0.0028   0.8294   0.5683
  -1.750  -0.1861   0.00519   0.00100  -0.0023   0.8114   0.5867
  -1.500  -0.1597   0.00517   0.00096  -0.0019   0.7943   0.6041
  -1.250  -0.1331   0.00516   0.00093  -0.0016   0.7780   0.6208
  -1.000  -0.1065   0.00514   0.00091  -0.0013   0.7628   0.6371
  -0.750  -0.0799   0.00512   0.00089  -0.0010   0.7479   0.6532
  -0.500  -0.0532   0.00511   0.00088  -0.0006   0.7327   0.6693
  -0.250  -0.0266   0.00510   0.00087  -0.0003   0.7172   0.6854
   0.000   0.0000   0.00510   0.00087   0.0000   0.7014   0.7015
   0.250   0.0266   0.00510   0.00087   0.0003   0.6854   0.7172
   0.500   0.0533   0.00511   0.00088   0.0006   0.6693   0.7327
   0.750   0.0799   0.00512   0.00089   0.0010   0.6532   0.7479
   1.000   0.1065   0.00514   0.00091   0.0013   0.6371   0.7629
   1.250   0.1331   0.00516   0.00093   0.0016   0.6207   0.7780
   1.500   0.1597   0.00517   0.00096   0.0019   0.6039   0.7942
   1.750   0.1861   0.00519   0.00100   0.0023   0.5865   0.8114
   2.000   0.2123   0.00521   0.00105   0.0028   0.5689   0.8294
   2.250   0.2383   0.00525   0.00111   0.0032   0.5498   0.8483
   2.500   0.2644   0.00529   0.00117   0.0037   0.5276   0.8682
   2.750   0.2903   0.00536   0.00124   0.0042   0.5026   0.8885
   3.000   0.3160   0.00549   0.00133   0.0047   0.4665   0.9099
   3.250   0.3423   0.00575   0.00146   0.0050   0.4066   0.9300
   3.500   0.3686   0.00641   0.00170   0.0050   0.2920   0.9479
   3.750   0.3986   0.00705   0.00198   0.0041   0.1971   0.9606
   4.000   0.4293   0.00759   0.00225   0.0032   0.1287   0.9707
   4.250   0.4639   0.00806   0.00252   0.0014   0.0836   0.9761
   4.500   0.4947   0.00845   0.00278   0.0005   0.0560   0.9831
   4.750   0.5304   0.00878   0.00305  -0.0014   0.0415   0.9861
   5.000   0.5646   0.00912   0.00337  -0.0029   0.0324   0.9898
   5.250   0.5971   0.00953   0.00375  -0.0041   0.0256   0.9937
   5.500   0.6322   0.00980   0.00404  -0.0059   0.0229   0.9964
   5.750   0.6670   0.01017   0.00440  -0.0076   0.0198   0.9989
   6.000   0.6942   0.01070   0.00499  -0.0077   0.0177   1.0000
   6.250   0.7155   0.01096   0.00528  -0.0064   0.0167   1.0000
   6.500   0.7368   0.01125   0.00557  -0.0052   0.0154   1.0000
   6.750   0.7576   0.01162   0.00595  -0.0040   0.0142   1.0000
   7.000   0.7737   0.01258   0.00701  -0.0018   0.0129   1.0000
   7.250   0.7955   0.01291   0.00739  -0.0007   0.0126   1.0000
   7.500   0.8168   0.01333   0.00786   0.0004   0.0120   1.0000
   7.750   0.8376   0.01383   0.00841   0.0017   0.0114   1.0000
   8.000   0.8583   0.01435   0.00898   0.0029   0.0110   1.0000
   8.250   0.8791   0.01487   0.00953   0.0040   0.0105   1.0000
   8.500   0.8991   0.01548   0.01019   0.0053   0.0101   1.0000
   8.750   0.9144   0.01674   0.01156   0.0072   0.0095   1.0000
   9.000   0.9291   0.01823   0.01322   0.0092   0.0091   1.0000
   9.250   0.9496   0.01884   0.01392   0.0103   0.0089   1.0000
   9.500   0.9698   0.01946   0.01462   0.0114   0.0085   1.0000
   9.750   0.9869   0.02055   0.01585   0.0129   0.0083   1.0000
  10.000   1.0040   0.02160   0.01702   0.0143   0.0081   1.0000
  10.250   1.0198   0.02277   0.01833   0.0158   0.0079   1.0000
  10.500   1.0339   0.02409   0.01981   0.0175   0.0077   1.0000
  10.750   1.0474   0.02532   0.02119   0.0191   0.0075   1.0000
  11.000   1.0569   0.02695   0.02300   0.0212   0.0074   1.0000
  11.250   1.0703   0.02780   0.02393   0.0227   0.0072   1.0000
  11.500   1.0744   0.02963   0.02595   0.0252   0.0071   1.0000
  11.750   1.0748   0.03105   0.02750   0.0284   0.0070   1.0000
  12.000   1.0708   0.03280   0.02940   0.0316   0.0070   1.0000
  12.250   1.0713   0.03423   0.03092   0.0337   0.0068   1.0000
  12.500   1.0644   0.03659   0.03343   0.0354   0.0068   1.0000
  12.750   1.0571   0.03927   0.03626   0.0362   0.0067   1.0000
  13.000   1.0400   0.04352   0.04071   0.0358   0.0067   1.0000
  13.250   1.0176   0.04926   0.04671   0.0337   0.0068   1.0000
  13.500   1.0039   0.05438   0.05196   0.0307   0.0067   1.0000
  13.750   0.9863   0.06079   0.05851   0.0265   0.0066   1.0000
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