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RAE 103 AIRFOIL (rae103-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: RAE 103 AIRFOIL (rae103-il)
Reynolds number: 1,000,000
Max Cl/Cd: 62.23 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae103-il-1000000.txt
Download as CSV file: xf-rae103-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.7714   0.09112   0.08954  -0.0121   1.0000   0.0076
 -12.500  -0.7666   0.08745   0.08588  -0.0144   1.0000   0.0077
 -12.250  -0.9275   0.04775   0.04541  -0.0384   1.0000   0.0065
 -11.750  -0.9505   0.04101   0.03832  -0.0381   1.0000   0.0067
 -11.500  -0.9657   0.03792   0.03503  -0.0359   1.0000   0.0067
 -11.000  -0.9968   0.03256   0.02917  -0.0273   1.0000   0.0069
 -10.750  -1.0044   0.02949   0.02578  -0.0236   1.0000   0.0069
 -10.500  -1.0095   0.02610   0.02204  -0.0199   1.0000   0.0071
 -10.250  -1.0020   0.02412   0.01985  -0.0174   1.0000   0.0073
 -10.000  -0.9886   0.02287   0.01848  -0.0156   1.0000   0.0075
  -9.750  -0.9751   0.02145   0.01689  -0.0137   1.0000   0.0076
  -9.500  -0.9583   0.02053   0.01588  -0.0121   1.0000   0.0078
  -9.250  -0.9416   0.01953   0.01475  -0.0105   1.0000   0.0080
  -9.000  -0.9237   0.01871   0.01383  -0.0091   1.0000   0.0082
  -8.750  -0.9060   0.01781   0.01283  -0.0075   1.0000   0.0085
  -8.500  -0.8878   0.01698   0.01190  -0.0059   1.0000   0.0088
  -8.250  -0.8686   0.01633   0.01118  -0.0045   1.0000   0.0092
  -8.000  -0.8489   0.01580   0.01058  -0.0032   1.0000   0.0096
  -7.750  -0.8285   0.01537   0.01010  -0.0019   1.0000   0.0099
  -7.500  -0.8141   0.01422   0.00882   0.0005   1.0000   0.0103
  -7.250  -0.8006   0.01316   0.00765   0.0030   1.0000   0.0110
  -7.000  -0.7824   0.01269   0.00717   0.0048   1.0000   0.0117
  -6.750  -0.7642   0.01229   0.00673   0.0065   1.0000   0.0123
  -6.500  -0.7305   0.01181   0.00621   0.0049   0.9981   0.0134
  -6.250  -0.6964   0.01144   0.00581   0.0033   0.9956   0.0142
  -6.000  -0.6653   0.01068   0.00495   0.0022   0.9923   0.0160
  -5.750  -0.6326   0.01030   0.00458   0.0009   0.9885   0.0182
  -5.500  -0.5981   0.01003   0.00430  -0.0008   0.9853   0.0201
  -5.250  -0.5655   0.00951   0.00374  -0.0020   0.9812   0.0242
  -5.000  -0.5330   0.00922   0.00345  -0.0032   0.9754   0.0281
  -4.750  -0.4980   0.00883   0.00309  -0.0050   0.9707   0.0369
  -4.500  -0.4660   0.00849   0.00280  -0.0061   0.9617   0.0498
  -4.250  -0.4335   0.00812   0.00252  -0.0073   0.9516   0.0749
  -4.000  -0.4046   0.00770   0.00225  -0.0078   0.9371   0.1184
  -3.750  -0.3794   0.00726   0.00201  -0.0075   0.9194   0.1760
  -3.500  -0.3569   0.00675   0.00176  -0.0066   0.9008   0.2585
  -3.250  -0.3361   0.00617   0.00152  -0.0055   0.8827   0.3623
  -3.000  -0.3162   0.00556   0.00129  -0.0041   0.8656   0.4812
  -2.750  -0.2931   0.00528   0.00121  -0.0032   0.8506   0.5579
  -2.500  -0.2678   0.00519   0.00115  -0.0026   0.8373   0.5927
  -2.250  -0.2417   0.00514   0.00110  -0.0022   0.8250   0.6146
  -2.000  -0.2153   0.00511   0.00106  -0.0019   0.8134   0.6329
  -1.750  -0.1886   0.00508   0.00103  -0.0016   0.8024   0.6490
  -1.500  -0.1618   0.00506   0.00100  -0.0013   0.7921   0.6634
  -1.250  -0.1351   0.00506   0.00097  -0.0010   0.7823   0.6765
  -1.000  -0.1081   0.00504   0.00096  -0.0008   0.7723   0.6887
  -0.750  -0.0810   0.00504   0.00094  -0.0006   0.7627   0.7002
  -0.250  -0.0270   0.00504   0.00093  -0.0002   0.7428   0.7222
   0.000   0.0000   0.00503   0.00093   0.0000   0.7324   0.7324
   0.250   0.0271   0.00504   0.00093   0.0002   0.7221   0.7428
   0.750   0.0810   0.00504   0.00094   0.0006   0.7003   0.7628
   1.000   0.1081   0.00504   0.00096   0.0008   0.6888   0.7724
   1.250   0.1351   0.00506   0.00097   0.0010   0.6765   0.7823
   1.500   0.1618   0.00506   0.00100   0.0013   0.6634   0.7921
   1.750   0.1886   0.00508   0.00103   0.0016   0.6494   0.8024
   2.000   0.2153   0.00511   0.00106   0.0019   0.6331   0.8134
   2.250   0.2417   0.00514   0.00110   0.0022   0.6147   0.8250
   2.500   0.2677   0.00519   0.00115   0.0026   0.5919   0.8373
   2.750   0.2931   0.00528   0.00121   0.0032   0.5576   0.8507
   3.000   0.3159   0.00558   0.00129   0.0041   0.4762   0.8656
   3.250   0.3361   0.00617   0.00152   0.0055   0.3618   0.8827
   3.500   0.3571   0.00673   0.00176   0.0066   0.2619   0.9007
   3.750   0.3794   0.00726   0.00201   0.0075   0.1759   0.9195
   4.000   0.4045   0.00771   0.00226   0.0078   0.1167   0.9372
   4.250   0.4335   0.00812   0.00252   0.0073   0.0750   0.9516
   4.500   0.4659   0.00850   0.00280   0.0061   0.0497   0.9617
   4.750   0.4979   0.00883   0.00309   0.0050   0.0370   0.9707
   5.000   0.5329   0.00922   0.00345   0.0032   0.0281   0.9754
   5.250   0.5654   0.00951   0.00374   0.0020   0.0242   0.9813
   5.500   0.5980   0.01003   0.00430   0.0008   0.0201   0.9853
   5.750   0.6325   0.01031   0.00459  -0.0009   0.0182   0.9886
   6.000   0.6652   0.01069   0.00496  -0.0022   0.0161   0.9923
   6.250   0.6963   0.01145   0.00582  -0.0033   0.0142   0.9956
   6.500   0.7303   0.01184   0.00624  -0.0049   0.0133   0.9981
   6.750   0.7640   0.01231   0.00675  -0.0065   0.0124   1.0000
   7.000   0.7825   0.01268   0.00715  -0.0048   0.0117   1.0000
   7.250   0.8008   0.01314   0.00764  -0.0031   0.0112   1.0000
   7.500   0.8160   0.01400   0.00858  -0.0008   0.0105   1.0000
   7.750   0.8293   0.01527   0.00998   0.0017   0.0099   1.0000
   8.000   0.8486   0.01584   0.01062   0.0032   0.0097   1.0000
   8.250   0.8689   0.01629   0.01113   0.0045   0.0092   1.0000
   8.500   0.8879   0.01696   0.01189   0.0059   0.0088   1.0000
   8.750   0.9059   0.01782   0.01284   0.0075   0.0085   1.0000
   9.000   0.9243   0.01860   0.01371   0.0090   0.0082   1.0000
   9.250   0.9418   0.01948   0.01470   0.0105   0.0080   1.0000
   9.500   0.9591   0.02037   0.01570   0.0120   0.0078   1.0000
   9.750   0.9755   0.02134   0.01676   0.0136   0.0076   1.0000
  10.000   0.9896   0.02264   0.01821   0.0154   0.0075   1.0000
  10.250   1.0029   0.02392   0.01961   0.0173   0.0072   1.0000
  10.500   1.0075   0.02635   0.02231   0.0201   0.0071   1.0000
  10.750   1.0029   0.02966   0.02597   0.0237   0.0069   1.0000
  11.000   0.9825   0.03383   0.03057   0.0289   0.0068   1.0000
  11.500   0.9608   0.03840   0.03553   0.0362   0.0067   1.0000
  11.750   0.9378   0.04233   0.03970   0.0383   0.0067   1.0000
  12.000   0.9342   0.04470   0.04220   0.0387   0.0067   1.0000
  12.250   0.9113   0.04982   0.04753   0.0376   0.0067   1.0000
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