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RAF 38 AIRFOIL (raf38-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: RAF 38 AIRFOIL (raf38-il)
Reynolds number: 1,000,000
Max Cl/Cd: 98.93 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf38-il-1000000-n5.txt
Download as CSV file: xf-raf38-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.000  -0.8779   0.10138   0.09891  -0.0342   1.0000   0.0076
 -16.750  -0.9880   0.07869   0.07592  -0.0473   1.0000   0.0071
 -16.500  -1.0887   0.05683   0.05370  -0.0613   1.0000   0.0068
 -16.250  -1.1299   0.04563   0.04224  -0.0701   1.0000   0.0068
 -16.000  -1.1428   0.04018   0.03663  -0.0741   1.0000   0.0068
 -15.750  -1.1553   0.03574   0.03204  -0.0766   1.0000   0.0068
 -15.500  -1.1582   0.03304   0.02921  -0.0772   1.0000   0.0069
 -15.250  -1.1639   0.03054   0.02659  -0.0768   1.0000   0.0070
 -15.000  -1.1676   0.02857   0.02451  -0.0754   1.0000   0.0071
 -14.750  -1.1681   0.02709   0.02293  -0.0733   1.0000   0.0072
 -14.500  -1.1680   0.02583   0.02159  -0.0705   1.0000   0.0073
 -14.250  -1.1662   0.02487   0.02054  -0.0673   1.0000   0.0074
 -14.000  -1.1631   0.02403   0.01963  -0.0639   1.0000   0.0075
 -13.750  -1.1544   0.02317   0.01869  -0.0614   1.0000   0.0077
 -13.500  -1.1439   0.02239   0.01784  -0.0591   1.0000   0.0078
 -13.250  -1.1325   0.02164   0.01702  -0.0569   1.0000   0.0080
 -13.000  -1.1201   0.02094   0.01625  -0.0546   1.0000   0.0082
 -12.750  -1.1067   0.02031   0.01555  -0.0525   1.0000   0.0084
 -12.250  -1.0586   0.01891   0.01400  -0.0525   0.9962   0.0088
 -12.000  -1.0341   0.01813   0.01316  -0.0526   0.9910   0.0092
 -11.750  -1.0071   0.01742   0.01238  -0.0531   0.9859   0.0095
 -11.500  -0.9798   0.01679   0.01170  -0.0536   0.9795   0.0100
 -11.250  -0.9482   0.01620   0.01106  -0.0549   0.9734   0.0105
 -11.000  -0.9135   0.01562   0.01041  -0.0568   0.9661   0.0109
 -10.750  -0.8769   0.01500   0.00972  -0.0592   0.9559   0.0115
 -10.500  -0.8381   0.01436   0.00901  -0.0620   0.9400   0.0122
 -10.250  -0.8050   0.01390   0.00844  -0.0635   0.9110   0.0129
 -10.000  -0.7808   0.01361   0.00800  -0.0628   0.8775   0.0136
  -9.750  -0.7593   0.01331   0.00756  -0.0617   0.8520   0.0144
  -9.500  -0.7374   0.01298   0.00714  -0.0607   0.8347   0.0153
  -9.250  -0.7145   0.01268   0.00676  -0.0598   0.8213   0.0164
  -9.000  -0.6912   0.01241   0.00640  -0.0590   0.8098   0.0174
  -8.750  -0.6680   0.01209   0.00603  -0.0581   0.7990   0.0189
  -8.500  -0.6440   0.01181   0.00570  -0.0574   0.7893   0.0206
  -8.250  -0.6200   0.01154   0.00538  -0.0567   0.7806   0.0228
  -8.000  -0.5954   0.01126   0.00508  -0.0562   0.7727   0.0256
  -7.750  -0.5708   0.01103   0.00483  -0.0556   0.7653   0.0291
  -7.500  -0.5453   0.01082   0.00461  -0.0551   0.7583   0.0323
  -7.250  -0.5199   0.01064   0.00442  -0.0546   0.7508   0.0357
  -7.000  -0.4939   0.01049   0.00427  -0.0543   0.7441   0.0390
  -6.750  -0.4676   0.01037   0.00410  -0.0539   0.7370   0.0408
  -6.500  -0.4413   0.01027   0.00394  -0.0536   0.7301   0.0417
  -6.250  -0.4157   0.01008   0.00371  -0.0531   0.7216   0.0440
  -6.000  -0.3897   0.00993   0.00354  -0.0527   0.7133   0.0460
  -5.750  -0.3635   0.00981   0.00339  -0.0523   0.7043   0.0479
  -5.500  -0.3372   0.00970   0.00323  -0.0520   0.6963   0.0494
  -5.250  -0.3107   0.00960   0.00308  -0.0517   0.6880   0.0507
  -5.000  -0.2839   0.00951   0.00294  -0.0514   0.6820   0.0516
  -4.750  -0.2569   0.00942   0.00283  -0.0512   0.6762   0.0522
  -4.500  -0.2306   0.00927   0.00263  -0.0508   0.6703   0.0537
  -4.250  -0.2042   0.00911   0.00245  -0.0504   0.6651   0.0558
  -4.000  -0.1775   0.00898   0.00230  -0.0502   0.6592   0.0573
  -3.750  -0.1508   0.00887   0.00217  -0.0499   0.6536   0.0588
  -3.500  -0.1239   0.00877   0.00204  -0.0496   0.6491   0.0602
  -3.250  -0.0967   0.00867   0.00194  -0.0494   0.6440   0.0616
  -3.000  -0.0697   0.00860   0.00183  -0.0492   0.6383   0.0631
  -2.750  -0.0427   0.00853   0.00174  -0.0489   0.6332   0.0646
  -2.500  -0.0156   0.00843   0.00164  -0.0487   0.6275   0.0690
  -2.250   0.0113   0.00834   0.00155  -0.0485   0.6220   0.0740
  -2.000   0.0378   0.00821   0.00147  -0.0482   0.6172   0.0892
  -1.750   0.0633   0.00794   0.00137  -0.0477   0.6121   0.1373
  -1.500   0.0894   0.00778   0.00131  -0.0474   0.6061   0.1705
  -1.250   0.1160   0.00769   0.00127  -0.0471   0.6004   0.1911
  -1.000   0.1430   0.00761   0.00123  -0.0469   0.5940   0.2088
  -0.750   0.1693   0.00751   0.00119  -0.0466   0.5879   0.2351
  -0.500   0.1953   0.00733   0.00115  -0.0462   0.5823   0.2773
  -0.250   0.2210   0.00716   0.00113  -0.0458   0.5756   0.3282
   0.000   0.2461   0.00698   0.00111  -0.0453   0.5688   0.3884
   0.250   0.2717   0.00682   0.00111  -0.0448   0.5607   0.4435
   0.500   0.2970   0.00670   0.00112  -0.0443   0.5526   0.4930
   0.750   0.3228   0.00664   0.00113  -0.0439   0.5413   0.5267
   1.000   0.3482   0.00660   0.00114  -0.0434   0.5276   0.5613
   1.250   0.3728   0.00656   0.00117  -0.0427   0.5114   0.6030
   1.500   0.3955   0.00646   0.00122  -0.0416   0.4941   0.6708
   1.750   0.4181   0.00641   0.00129  -0.0405   0.4770   0.7302
   2.000   0.4401   0.00639   0.00137  -0.0392   0.4581   0.7841
   2.250   0.4625   0.00637   0.00146  -0.0379   0.4426   0.8337
   2.500   0.4875   0.00634   0.00156  -0.0372   0.4314   0.8840
   2.750   0.5189   0.00641   0.00168  -0.0379   0.4213   0.9199
   3.000   0.5566   0.00657   0.00182  -0.0400   0.4084   0.9426
   3.250   0.5960   0.00673   0.00195  -0.0426   0.3968   0.9565
   3.500   0.6318   0.00688   0.00207  -0.0444   0.3860   0.9652
   3.750   0.6656   0.00704   0.00218  -0.0458   0.3730   0.9697
   4.000   0.6951   0.00721   0.00231  -0.0462   0.3611   0.9753
   4.250   0.7275   0.00740   0.00244  -0.0473   0.3461   0.9784
   4.500   0.7565   0.00765   0.00260  -0.0477   0.3211   0.9828
   4.750   0.7875   0.00796   0.00279  -0.0487   0.2940   0.9865
   5.000   0.8198   0.00836   0.00303  -0.0500   0.2611   0.9902
   5.250   0.8501   0.00883   0.00333  -0.0509   0.2279   0.9942
   5.500   0.8841   0.00918   0.00358  -0.0526   0.2055   0.9969
   5.750   0.9170   0.00953   0.00383  -0.0540   0.1839   0.9991
   6.000   0.9424   0.00993   0.00411  -0.0539   0.1589   1.0000
   6.250   0.9581   0.01040   0.00443  -0.0517   0.1292   1.0000
   6.500   0.9698   0.01108   0.00488  -0.0488   0.0895   1.0000
   6.750   0.9861   0.01151   0.00522  -0.0467   0.0737   1.0000
   7.000   1.0042   0.01184   0.00552  -0.0450   0.0666   1.0000
   7.250   1.0237   0.01209   0.00577  -0.0434   0.0634   1.0000
   7.500   1.0427   0.01237   0.00604  -0.0418   0.0601   1.0000
   7.750   1.0612   0.01267   0.00634  -0.0402   0.0568   1.0000
   8.000   1.0805   0.01293   0.00661  -0.0387   0.0548   1.0000
   8.250   1.0999   0.01317   0.00688  -0.0372   0.0528   1.0000
   8.500   1.1184   0.01347   0.00717  -0.0356   0.0500   1.0000
   8.750   1.1354   0.01382   0.00752  -0.0337   0.0462   1.0000
   9.000   1.1534   0.01412   0.00783  -0.0321   0.0440   1.0000
   9.250   1.1706   0.01445   0.00817  -0.0303   0.0402   1.0000
   9.500   1.1828   0.01487   0.00855  -0.0276   0.0343   1.0000
  10.000   1.2046   0.01578   0.00944  -0.0219   0.0252   1.0000
  10.250   1.2156   0.01633   0.00997  -0.0193   0.0218   1.0000
  10.500   1.2286   0.01685   0.01051  -0.0172   0.0199   1.0000
  11.000   1.2530   0.01808   0.01178  -0.0131   0.0165   1.0000
  11.250   1.2655   0.01875   0.01247  -0.0113   0.0154   1.0000
  11.500   1.2769   0.01953   0.01328  -0.0095   0.0142   1.0000
  11.750   1.2896   0.02028   0.01408  -0.0080   0.0136   1.0000
  12.000   1.3013   0.02114   0.01497  -0.0065   0.0127   1.0000
  12.250   1.3123   0.02210   0.01597  -0.0051   0.0120   1.0000
  12.500   1.3227   0.02316   0.01707  -0.0038   0.0114   1.0000
  12.750   1.3343   0.02417   0.01813  -0.0028   0.0109   1.0000
  13.000   1.3448   0.02530   0.01931  -0.0017   0.0104   1.0000
  13.250   1.3547   0.02653   0.02060  -0.0007   0.0101   1.0000
  13.500   1.3634   0.02788   0.02200   0.0002   0.0098   1.0000
  13.750   1.3708   0.02939   0.02356   0.0011   0.0093   1.0000
  14.000   1.3788   0.03088   0.02511   0.0019   0.0090   1.0000
  14.250   1.3869   0.03240   0.02669   0.0026   0.0086   1.0000
  14.500   1.3931   0.03413   0.02848   0.0032   0.0084   1.0000
  14.750   1.3997   0.03585   0.03027   0.0038   0.0081   1.0000
  15.000   1.4044   0.03778   0.03225   0.0043   0.0079   1.0000
  15.250   1.4079   0.03986   0.03440   0.0047   0.0076   1.0000
  15.500   1.4107   0.04209   0.03669   0.0051   0.0075   1.0000
  15.750   1.4111   0.04460   0.03928   0.0053   0.0073   1.0000
  16.000   1.4139   0.04695   0.04171   0.0054   0.0071   1.0000
  16.250   1.4153   0.04950   0.04435   0.0054   0.0070   1.0000
  16.500   1.4161   0.05221   0.04713   0.0053   0.0069   1.0000
  16.750   1.4164   0.05501   0.05002   0.0050   0.0067   1.0000
  17.000   1.4157   0.05802   0.05311   0.0047   0.0066   1.0000
  17.250   1.4147   0.06115   0.05632   0.0042   0.0064   1.0000
  17.500   1.4125   0.06446   0.05971   0.0035   0.0063   1.0000
  17.750   1.4077   0.06819   0.06353   0.0027   0.0062   1.0000
  18.000   1.4045   0.07177   0.06719   0.0019   0.0061   1.0000
  18.250   1.3976   0.07595   0.07147   0.0008   0.0060   1.0000
  18.500   1.3924   0.07991   0.07551  -0.0004   0.0059   1.0000
  18.750   1.3829   0.08458   0.08027  -0.0018   0.0058   1.0000
  19.000   1.3735   0.08933   0.08512  -0.0033   0.0057   1.0000
  19.250   1.3602   0.09473   0.09062  -0.0052   0.0056   1.0000
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