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RAF 38 AIRFOIL (raf38-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: RAF 38 AIRFOIL (raf38-il)
Reynolds number: 500,000
Max Cl/Cd: 90.54 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf38-il-500000-n5.txt
Download as CSV file: xf-raf38-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 38 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
  ------ -------- --------- --------- -------- -------- --------
 -16.500  -0.7122   0.12374   0.12094  -0.0233   1.0000   0.0109
 -16.250  -0.7546   0.11079   0.10787  -0.0299   1.0000   0.0109
 -16.000  -0.7926   0.09959   0.09659  -0.0358   1.0000   0.0108
 -15.750  -0.8395   0.08744   0.08432  -0.0425   1.0000   0.0106
 -15.500  -0.8913   0.07460   0.07132  -0.0499   1.0000   0.0105
 -15.250  -0.9410   0.06181   0.05834  -0.0580   1.0000   0.0102
 -15.000  -0.9754   0.05143   0.04774  -0.0657   1.0000   0.0101
 -14.750  -0.9958   0.04421   0.04032  -0.0713   1.0000   0.0100
 -14.500  -1.0088   0.03928   0.03521  -0.0746   1.0000   0.0102
 -14.250  -1.0191   0.03566   0.03143  -0.0759   1.0000   0.0102
 -14.000  -1.0227   0.03329   0.02893  -0.0756   1.0000   0.0104
 -13.750  -1.0266   0.03129   0.02680  -0.0743   1.0000   0.0105
 -13.500  -1.0273   0.02979   0.02518  -0.0722   1.0000   0.0107
 -13.250  -1.0284   0.02849   0.02376  -0.0693   1.0000   0.0109
 -13.000  -1.0290   0.02744   0.02259  -0.0658   1.0000   0.0111
 -12.750  -1.0288   0.02630   0.02136  -0.0623   1.0000   0.0113
 -12.500  -1.0236   0.02521   0.02020  -0.0595   1.0000   0.0116
 -12.250  -1.0153   0.02426   0.01917  -0.0569   1.0000   0.0118
 -12.000  -1.0053   0.02340   0.01821  -0.0545   1.0000   0.0121
 -11.750  -0.9936   0.02263   0.01736  -0.0522   1.0000   0.0124
 -11.500  -0.9818   0.02187   0.01651  -0.0499   1.0000   0.0128
 -11.250  -0.9616   0.02106   0.01561  -0.0492   0.9985   0.0133
 -11.000  -0.9329   0.02026   0.01469  -0.0502   0.9933   0.0138
 -10.750  -0.9061   0.01932   0.01367  -0.0509   0.9871   0.0145
 -10.500  -0.8784   0.01856   0.01286  -0.0515   0.9799   0.0153
 -10.250  -0.8480   0.01787   0.01207  -0.0526   0.9730   0.0162
 -10.000  -0.8158   0.01722   0.01131  -0.0540   0.9652   0.0171
  -9.750  -0.7841   0.01646   0.01050  -0.0554   0.9553   0.0183
  -9.500  -0.7497   0.01583   0.00980  -0.0572   0.9440   0.0197
  -9.250  -0.7140   0.01525   0.00912  -0.0592   0.9297   0.0214
  -9.000  -0.6801   0.01468   0.00850  -0.0608   0.9109   0.0239
  -8.750  -0.6511   0.01428   0.00798  -0.0613   0.8885   0.0261
  -8.500  -0.6253   0.01396   0.00759  -0.0610   0.8684   0.0289
  -8.250  -0.6006   0.01372   0.00726  -0.0604   0.8518   0.0320
  -8.000  -0.5761   0.01350   0.00697  -0.0598   0.8378   0.0349
  -7.750  -0.5510   0.01335   0.00677  -0.0593   0.8255   0.0381
  -7.250  -0.5010   0.01303   0.00625  -0.0581   0.8043   0.0425
  -7.000  -0.4764   0.01280   0.00598  -0.0575   0.7958   0.0450
  -6.750  -0.4509   0.01264   0.00578  -0.0571   0.7874   0.0473
  -6.500  -0.4254   0.01249   0.00554  -0.0566   0.7797   0.0494
  -6.250  -0.3996   0.01235   0.00533  -0.0562   0.7717   0.0512
  -6.000  -0.3736   0.01224   0.00513  -0.0557   0.7646   0.0522
  -5.750  -0.3494   0.01189   0.00474  -0.0551   0.7575   0.0545
  -5.250  -0.2992   0.01145   0.00422  -0.0540   0.7411   0.0586
  -5.000  -0.2739   0.01129   0.00397  -0.0534   0.7321   0.0604
  -4.750  -0.2482   0.01112   0.00375  -0.0529   0.7229   0.0620
  -4.500  -0.2224   0.01098   0.00353  -0.0525   0.7156   0.0632
  -4.250  -0.1961   0.01082   0.00333  -0.0521   0.7090   0.0641
  -4.000  -0.1706   0.01062   0.00308  -0.0516   0.7027   0.0665
  -3.750  -0.1446   0.01045   0.00289  -0.0512   0.6969   0.0691
  -3.500  -0.1183   0.01029   0.00272  -0.0508   0.6909   0.0723
  -3.250  -0.0920   0.01018   0.00256  -0.0505   0.6852   0.0754
  -3.000  -0.0656   0.01003   0.00241  -0.0501   0.6795   0.0810
  -2.750  -0.0397   0.00985   0.00227  -0.0497   0.6732   0.0947
  -2.250   0.0109   0.00936   0.00205  -0.0488   0.6626   0.1724
  -2.000   0.0372   0.00923   0.00197  -0.0485   0.6568   0.1967
  -1.750   0.0632   0.00911   0.00189  -0.0481   0.6512   0.2189
  -1.250   0.1144   0.00872   0.00174  -0.0472   0.6391   0.2955
  -1.000   0.1384   0.00843   0.00170  -0.0466   0.6339   0.3719
  -0.750   0.1633   0.00820   0.00168  -0.0460   0.6281   0.4344
  -0.500   0.1885   0.00806   0.00165  -0.0454   0.6218   0.4797
  -0.250   0.2137   0.00792   0.00164  -0.0449   0.6157   0.5224
   0.000   0.2379   0.00773   0.00163  -0.0441   0.6089   0.5788
   0.250   0.2614   0.00757   0.00164  -0.0431   0.6028   0.6354
   0.500   0.2861   0.00745   0.00167  -0.0423   0.5963   0.6823
   0.750   0.3102   0.00735   0.00170  -0.0414   0.5893   0.7299
   1.000   0.3340   0.00722   0.00175  -0.0404   0.5821   0.7843
   1.250   0.3592   0.00711   0.00182  -0.0395   0.5739   0.8398
   1.500   0.3917   0.00710   0.00193  -0.0403   0.5649   0.8900
   1.750   0.4303   0.00719   0.00202  -0.0425   0.5521   0.9187
   2.000   0.4680   0.00732   0.00210  -0.0445   0.5359   0.9374
   2.250   0.5044   0.00746   0.00219  -0.0463   0.5189   0.9510
   2.500   0.5410   0.00763   0.00228  -0.0482   0.4995   0.9598
   2.750   0.5737   0.00781   0.00238  -0.0493   0.4821   0.9671
   3.000   0.6039   0.00799   0.00249  -0.0498   0.4667   0.9742
   3.250   0.6381   0.00815   0.00260  -0.0513   0.4541   0.9780
   3.500   0.6698   0.00833   0.00273  -0.0522   0.4414   0.9831
   3.750   0.7027   0.00853   0.00286  -0.0534   0.4256   0.9870
   4.000   0.7365   0.00873   0.00301  -0.0549   0.4099   0.9910
   4.250   0.7720   0.00890   0.00315  -0.0567   0.3984   0.9952
   4.500   0.8109   0.00908   0.00330  -0.0593   0.3834   0.9992
   4.750   0.8361   0.00928   0.00345  -0.0589   0.3676   1.0000
   5.000   0.8569   0.00947   0.00361  -0.0576   0.3527   1.0000
   5.250   0.8773   0.00969   0.00378  -0.0562   0.3360   1.0000
   5.500   0.8960   0.01000   0.00399  -0.0545   0.3099   1.0000
   5.750   0.9130   0.01042   0.00426  -0.0526   0.2772   1.0000
   6.000   0.9295   0.01087   0.00457  -0.0506   0.2485   1.0000
   6.250   0.9467   0.01129   0.00488  -0.0487   0.2264   1.0000
   6.500   0.9641   0.01169   0.00521  -0.0468   0.2069   1.0000
   6.750   0.9811   0.01211   0.00554  -0.0449   0.1857   1.0000
   7.000   0.9965   0.01262   0.00593  -0.0428   0.1599   1.0000
   7.250   1.0074   0.01336   0.00644  -0.0399   0.1183   1.0000
   7.500   1.0176   0.01412   0.00701  -0.0370   0.0876   1.0000
   7.750   1.0323   0.01463   0.00745  -0.0348   0.0767   1.0000
   8.000   1.0490   0.01501   0.00785  -0.0329   0.0717   1.0000
   8.250   1.0640   0.01546   0.00828  -0.0308   0.0671   1.0000
   8.500   1.0802   0.01583   0.00868  -0.0288   0.0637   1.0000
   8.750   1.0941   0.01623   0.00911  -0.0264   0.0608   1.0000
   9.000   1.1055   0.01668   0.00957  -0.0237   0.0577   1.0000
   9.250   1.1174   0.01713   0.01005  -0.0211   0.0549   1.0000
   9.500   1.1319   0.01753   0.01049  -0.0190   0.0523   1.0000
   9.750   1.1450   0.01802   0.01101  -0.0168   0.0489   1.0000
  10.000   1.1567   0.01862   0.01161  -0.0146   0.0447   1.0000
  10.250   1.1708   0.01915   0.01220  -0.0128   0.0418   1.0000
  10.500   1.1825   0.01983   0.01287  -0.0109   0.0364   1.0000
  10.750   1.1936   0.02060   0.01364  -0.0090   0.0319   1.0000
  11.000   1.2032   0.02150   0.01453  -0.0071   0.0278   1.0000
  11.250   1.2133   0.02243   0.01549  -0.0054   0.0250   1.0000
  11.500   1.2220   0.02352   0.01660  -0.0038   0.0227   1.0000
  11.750   1.2313   0.02462   0.01777  -0.0023   0.0209   1.0000
  12.000   1.2399   0.02584   0.01903  -0.0009   0.0193   1.0000
  12.250   1.2473   0.02720   0.02043   0.0003   0.0181   1.0000
  12.500   1.2554   0.02856   0.02186   0.0015   0.0171   1.0000
  12.750   1.2636   0.02996   0.02333   0.0025   0.0163   1.0000
  13.000   1.2707   0.03149   0.02493   0.0034   0.0155   1.0000
  13.250   1.2764   0.03319   0.02668   0.0042   0.0149   1.0000
  13.500   1.2803   0.03510   0.02864   0.0050   0.0142   1.0000
  13.750   1.2864   0.03687   0.03050   0.0057   0.0137   1.0000
  14.000   1.2908   0.03882   0.03255   0.0063   0.0133   1.0000
  14.250   1.2947   0.04087   0.03468   0.0067   0.0127   1.0000
  14.500   1.2965   0.04319   0.03708   0.0071   0.0123   1.0000
  14.750   1.2985   0.04554   0.03950   0.0074   0.0120   1.0000
  15.000   1.2979   0.04824   0.04228   0.0075   0.0116   1.0000
  15.250   1.2976   0.05103   0.04515   0.0075   0.0113   1.0000
  15.500   1.2988   0.05371   0.04793   0.0073   0.0111   1.0000
  15.750   1.2982   0.05666   0.05098   0.0071   0.0107   1.0000
  16.000   1.2975   0.05972   0.05414   0.0067   0.0104   1.0000
  16.250   1.2950   0.06310   0.05762   0.0061   0.0103   1.0000
  16.500   1.2932   0.06645   0.06106   0.0054   0.0100   1.0000
  16.750   1.2880   0.07033   0.06504   0.0044   0.0099   1.0000
  17.000   1.2853   0.07397   0.06877   0.0035   0.0096   1.0000
  17.250   1.2789   0.07820   0.07310   0.0023   0.0095   1.0000
  17.500   1.2711   0.08269   0.07769   0.0009   0.0093   1.0000
  17.750   1.2621   0.08747   0.08256  -0.0007   0.0092   1.0000
  18.000   1.2548   0.09206   0.08726  -0.0023   0.0091   1.0000
  18.250   1.2482   0.09659   0.09190  -0.0039   0.0090   1.0000
  18.500   1.2404   0.10138   0.09681  -0.0058   0.0089   1.0000
  18.750   1.2328   0.10627   0.10181  -0.0077   0.0087   1.0000
  19.000   1.2238   0.11147   0.10712  -0.0099   0.0086   1.0000
  19.250   1.2145   0.11675   0.11251  -0.0122   0.0085   1.0000
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