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RAF 27 AIRFOIL (raf27-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: RAF 27 AIRFOIL (raf27-il)
Reynolds number: 200,000
Max Cl/Cd: 49.1 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf27-il-200000.txt
Download as CSV file: xf-raf27-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 27 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.5094   0.12403   0.12047  -0.0025   1.0000   0.0635
 -12.000  -0.6558   0.11795   0.11424  -0.0073   1.0000   0.0578
 -11.750  -0.6317   0.11853   0.11476  -0.0022   1.0000   0.0605
 -11.500  -0.6283   0.11503   0.11127  -0.0031   1.0000   0.0629
 -11.250  -0.6313   0.11021   0.10647  -0.0055   1.0000   0.0653
  -9.750  -0.8527   0.05266   0.04799  -0.0293   1.0000   0.0368
  -9.500  -0.8512   0.05144   0.04639  -0.0261   1.0000   0.0356
  -9.250  -0.8568   0.04718   0.04181  -0.0234   1.0000   0.0357
  -9.000  -0.8511   0.04306   0.03749  -0.0215   1.0000   0.0349
  -8.750  -0.8488   0.03933   0.03341  -0.0187   1.0000   0.0347
  -8.500  -0.8434   0.03577   0.02947  -0.0160   1.0000   0.0346
  -8.250  -0.8338   0.03287   0.02616  -0.0134   1.0000   0.0347
  -8.000  -0.8206   0.03074   0.02365  -0.0110   1.0000   0.0351
  -7.750  -0.8071   0.02761   0.02016  -0.0089   1.0000   0.0360
  -7.500  -0.7897   0.02531   0.01779  -0.0076   1.0000   0.0383
  -7.250  -0.7704   0.02405   0.01642  -0.0061   1.0000   0.0406
  -7.000  -0.7501   0.02258   0.01477  -0.0046   1.0000   0.0426
  -6.750  -0.7292   0.02138   0.01337  -0.0031   1.0000   0.0447
  -6.500  -0.7103   0.01970   0.01166  -0.0016   1.0000   0.0483
  -6.250  -0.6908   0.01882   0.01077   0.0000   1.0000   0.0523
  -6.000  -0.6708   0.01798   0.00984   0.0016   1.0000   0.0560
  -5.750  -0.6539   0.01685   0.00875   0.0035   1.0000   0.0611
  -5.500  -0.6346   0.01623   0.00809   0.0052   1.0000   0.0678
  -5.250  -0.6180   0.01532   0.00722   0.0073   1.0000   0.0752
  -5.000  -0.6007   0.01456   0.00649   0.0092   1.0000   0.0872
  -4.750  -0.5849   0.01363   0.00571   0.0114   1.0000   0.1133
  -4.500  -0.5733   0.01232   0.00507   0.0140   1.0000   0.2189
  -4.250  -0.5579   0.01159   0.00472   0.0160   1.0000   0.3081
  -4.000  -0.5413   0.01108   0.00449   0.0180   1.0000   0.3737
  -3.750  -0.5243   0.01068   0.00435   0.0200   1.0000   0.4383
  -3.500  -0.5070   0.01037   0.00424   0.0220   1.0000   0.4953
  -3.250  -0.4897   0.01011   0.00417   0.0241   1.0000   0.5470
  -3.000  -0.4730   0.00989   0.00416   0.0263   1.0000   0.6010
  -2.750  -0.4567   0.00975   0.00422   0.0287   1.0000   0.6546
  -2.500  -0.4398   0.00966   0.00427   0.0310   1.0000   0.6982
  -2.250  -0.4228   0.00960   0.00432   0.0331   1.0000   0.7365
  -2.000  -0.3955   0.00960   0.00444   0.0333   0.9970   0.7795
  -1.750  -0.3558   0.00966   0.00462   0.0312   0.9904   0.8217
  -1.500  -0.3131   0.00976   0.00478   0.0284   0.9845   0.8563
  -1.250  -0.2699   0.00983   0.00486   0.0254   0.9781   0.8838
  -1.000  -0.2198   0.00997   0.00499   0.0211   0.9735   0.9050
  -0.750  -0.1650   0.01013   0.00512   0.0158   0.9702   0.9216
  -0.500  -0.1139   0.01024   0.00521   0.0112   0.9634   0.9349
  -0.250  -0.0570   0.01031   0.00526   0.0056   0.9581   0.9446
   0.000   0.0001   0.01034   0.00529   0.0000   0.9516   0.9517
   0.250   0.0570   0.01031   0.00526  -0.0056   0.9446   0.9581
   0.500   0.1139   0.01023   0.00520  -0.0112   0.9348   0.9633
   0.750   0.1650   0.01013   0.00512  -0.0158   0.9214   0.9702
   1.000   0.2197   0.00997   0.00499  -0.0211   0.9050   0.9735
   1.250   0.2699   0.00983   0.00486  -0.0254   0.8839   0.9782
   1.500   0.3132   0.00976   0.00478  -0.0284   0.8565   0.9845
   1.750   0.3558   0.00966   0.00462  -0.0311   0.8214   0.9904
   2.000   0.3954   0.00960   0.00444  -0.0333   0.7787   0.9970
   2.250   0.4228   0.00960   0.00432  -0.0331   0.7364   1.0000
   2.500   0.4400   0.00966   0.00427  -0.0310   0.6989   1.0000
   2.750   0.4569   0.00975   0.00422  -0.0288   0.6556   1.0000
   3.000   0.4731   0.00989   0.00416  -0.0264   0.6013   1.0000
   3.250   0.4898   0.01011   0.00418  -0.0241   0.5470   1.0000
   3.500   0.5071   0.01037   0.00424  -0.0221   0.4955   1.0000
   3.750   0.5244   0.01068   0.00435  -0.0200   0.4384   1.0000
   4.000   0.5414   0.01108   0.00449  -0.0180   0.3736   1.0000
   4.250   0.5581   0.01159   0.00472  -0.0161   0.3083   1.0000
   4.500   0.5733   0.01233   0.00507  -0.0140   0.2179   1.0000
   4.750   0.5851   0.01363   0.00571  -0.0114   0.1133   1.0000
   5.000   0.6007   0.01458   0.00650  -0.0092   0.0871   1.0000
   5.250   0.6181   0.01532   0.00722  -0.0073   0.0752   1.0000
   5.500   0.6347   0.01624   0.00809  -0.0052   0.0678   1.0000
   5.750   0.6540   0.01685   0.00876  -0.0036   0.0613   1.0000
   6.000   0.6709   0.01798   0.00984  -0.0016   0.0560   1.0000
   6.250   0.6909   0.01881   0.01077   0.0000   0.0523   1.0000
   6.500   0.7104   0.01971   0.01166   0.0015   0.0483   1.0000
   6.750   0.7293   0.02141   0.01340   0.0031   0.0447   1.0000
   7.000   0.7502   0.02260   0.01479   0.0046   0.0426   1.0000
   7.250   0.7705   0.02407   0.01645   0.0061   0.0407   1.0000
   7.500   0.7898   0.02538   0.01787   0.0076   0.0385   1.0000
   7.750   0.8075   0.02742   0.01997   0.0089   0.0362   1.0000
   8.000   0.8206   0.03089   0.02380   0.0110   0.0352   1.0000
   8.250   0.8338   0.03289   0.02618   0.0134   0.0347   1.0000
   8.500   0.8433   0.03575   0.02946   0.0160   0.0345   1.0000
   8.750   0.8489   0.03925   0.03334   0.0187   0.0347   1.0000
   9.000   0.8513   0.04458   0.03893   0.0210   0.0355   1.0000
   9.250   0.8494   0.04818   0.04287   0.0238   0.0353   1.0000
   9.500   0.8453   0.05164   0.04664   0.0266   0.0353   1.0000
   9.750   0.8496   0.05289   0.04827   0.0296   0.0369   1.0000
  10.000   0.5759   0.07532   0.07194   0.0221   0.0768   1.0000
  10.250   0.5573   0.08295   0.07954   0.0182   0.0760   1.0000
  10.500   0.5461   0.08911   0.08567   0.0157   0.0749   1.0000
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