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RAE 101 AIRFOIL (rae101-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RAE 101 AIRFOIL (rae101-il)
Reynolds number: 500,000
Max Cl/Cd: 60.26 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae101-il-500000.txt
Download as CSV file: xf-rae101-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 101 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.7972   0.07888   0.07643  -0.0141   1.0000   0.0149
 -12.000  -0.8240   0.06925   0.06669  -0.0216   1.0000   0.0146
 -11.750  -0.8492   0.06146   0.05876  -0.0275   1.0000   0.0145
 -11.500  -0.8755   0.05495   0.05207  -0.0315   1.0000   0.0143
 -11.250  -0.9039   0.04939   0.04630  -0.0330   1.0000   0.0138
 -11.000  -0.9302   0.04508   0.04176  -0.0316   1.0000   0.0138
 -10.750  -0.9448   0.04249   0.03896  -0.0284   1.0000   0.0140
 -10.500  -0.9599   0.03864   0.03479  -0.0251   1.0000   0.0139
 -10.250  -0.9646   0.03510   0.03091  -0.0224   1.0000   0.0140
 -10.000  -0.9629   0.03189   0.02734  -0.0200   1.0000   0.0141
  -9.750  -0.9547   0.02931   0.02444  -0.0179   1.0000   0.0143
  -9.500  -0.9421   0.02724   0.02209  -0.0162   1.0000   0.0147
  -9.250  -0.9269   0.02541   0.02001  -0.0146   1.0000   0.0150
  -9.000  -0.9089   0.02414   0.01854  -0.0133   1.0000   0.0154
  -8.750  -0.8912   0.02257   0.01676  -0.0120   1.0000   0.0157
  -8.500  -0.8770   0.02005   0.01408  -0.0102   1.0000   0.0166
  -8.250  -0.8571   0.01916   0.01315  -0.0092   1.0000   0.0173
  -8.000  -0.8360   0.01849   0.01242  -0.0082   1.0000   0.0183
  -7.750  -0.8145   0.01785   0.01171  -0.0072   1.0000   0.0195
  -7.500  -0.7935   0.01710   0.01087  -0.0060   1.0000   0.0204
  -7.250  -0.7715   0.01654   0.01022  -0.0049   1.0000   0.0211
  -7.000  -0.7572   0.01490   0.00850  -0.0027   1.0000   0.0228
  -6.750  -0.7363   0.01432   0.00791  -0.0016   1.0000   0.0245
  -6.500  -0.7144   0.01388   0.00742  -0.0005   1.0000   0.0265
  -6.250  -0.6916   0.01354   0.00703   0.0005   1.0000   0.0281
  -6.000  -0.6743   0.01253   0.00598   0.0023   1.0000   0.0316
  -5.750  -0.6525   0.01211   0.00554   0.0035   1.0000   0.0348
  -5.500  -0.6313   0.01163   0.00501   0.0048   1.0000   0.0393
  -5.250  -0.6101   0.01118   0.00458   0.0060   1.0000   0.0457
  -5.000  -0.5892   0.01071   0.00414   0.0073   1.0000   0.0552
  -4.750  -0.5683   0.01029   0.00378   0.0085   1.0000   0.0709
  -4.500  -0.5482   0.00980   0.00344   0.0099   1.0000   0.1010
  -4.250  -0.5291   0.00925   0.00312   0.0113   1.0000   0.1514
  -4.000  -0.5072   0.00856   0.00281   0.0120   0.9992   0.2328
  -3.750  -0.4712   0.00782   0.00258   0.0096   0.9946   0.3520
  -3.500  -0.4349   0.00747   0.00243   0.0075   0.9891   0.4141
  -3.250  -0.3963   0.00724   0.00232   0.0051   0.9842   0.4555
  -3.000  -0.3605   0.00702   0.00221   0.0034   0.9773   0.4884
  -2.750  -0.3221   0.00684   0.00210   0.0011   0.9716   0.5180
  -2.500  -0.2868   0.00668   0.00200  -0.0004   0.9627   0.5445
  -2.250  -0.2505   0.00651   0.00191  -0.0022   0.9533   0.5704
  -2.000  -0.2160   0.00636   0.00182  -0.0035   0.9403   0.5953
  -1.750  -0.1846   0.00624   0.00174  -0.0040   0.9230   0.6193
  -1.500  -0.1555   0.00614   0.00167  -0.0040   0.9021   0.6428
  -1.250  -0.1284   0.00607   0.00162  -0.0036   0.8796   0.6651
  -1.000  -0.1024   0.00603   0.00157  -0.0029   0.8562   0.6872
  -0.750  -0.0767   0.00600   0.00153  -0.0022   0.8336   0.7081
  -0.500  -0.0512   0.00599   0.00151  -0.0014   0.8110   0.7286
  -0.250  -0.0256   0.00599   0.00149  -0.0007   0.7892   0.7489
   0.000   0.0000   0.00598   0.00149   0.0000   0.7684   0.7684
   0.250   0.0256   0.00599   0.00149   0.0007   0.7489   0.7892
   0.500   0.0512   0.00598   0.00151   0.0014   0.7286   0.8110
   0.750   0.0767   0.00600   0.00153   0.0022   0.7081   0.8336
   1.000   0.1024   0.00603   0.00157   0.0029   0.6873   0.8562
   1.250   0.1284   0.00607   0.00161   0.0036   0.6652   0.8796
   1.500   0.1555   0.00614   0.00167   0.0040   0.6427   0.9022
   1.750   0.1845   0.00624   0.00174   0.0040   0.6192   0.9230
   2.000   0.2159   0.00636   0.00182   0.0035   0.5951   0.9404
   2.250   0.2505   0.00651   0.00191   0.0022   0.5705   0.9532
   2.750   0.3221   0.00684   0.00210  -0.0011   0.5177   0.9717
   3.000   0.3605   0.00702   0.00221  -0.0034   0.4884   0.9774
   3.250   0.3963   0.00724   0.00232  -0.0051   0.4553   0.9843
   3.500   0.4349   0.00747   0.00243  -0.0075   0.4139   0.9892
   3.750   0.4712   0.00782   0.00258  -0.0096   0.3529   0.9946
   4.000   0.5074   0.00856   0.00281  -0.0120   0.2330   0.9993
   4.250   0.5288   0.00925   0.00312  -0.0112   0.1514   1.0000
   4.500   0.5480   0.00980   0.00344  -0.0098   0.1008   1.0000
   4.750   0.5681   0.01029   0.00378  -0.0085   0.0709   1.0000
   5.000   0.5890   0.01071   0.00414  -0.0072   0.0553   1.0000
   5.250   0.6099   0.01118   0.00458  -0.0059   0.0459   1.0000
   5.500   0.6311   0.01164   0.00501  -0.0047   0.0390   1.0000
   5.750   0.6523   0.01211   0.00554  -0.0034   0.0349   1.0000
   6.000   0.6741   0.01253   0.00598  -0.0023   0.0316   1.0000
   6.250   0.6915   0.01354   0.00703  -0.0005   0.0281   1.0000
   6.500   0.7142   0.01389   0.00743   0.0005   0.0266   1.0000
   6.750   0.7361   0.01433   0.00792   0.0016   0.0245   1.0000
   7.000   0.7571   0.01490   0.00851   0.0028   0.0229   1.0000
   7.250   0.7718   0.01649   0.01017   0.0049   0.0211   1.0000
   7.500   0.7935   0.01711   0.01087   0.0060   0.0204   1.0000
   7.750   0.8147   0.01783   0.01168   0.0071   0.0195   1.0000
   8.000   0.8360   0.01853   0.01246   0.0082   0.0184   1.0000
   8.250   0.8570   0.01923   0.01322   0.0092   0.0174   1.0000
   8.500   0.8771   0.02008   0.01411   0.0102   0.0166   1.0000
   8.750   0.8925   0.02223   0.01641   0.0118   0.0158   1.0000
   9.000   0.9090   0.02417   0.01857   0.0133   0.0154   1.0000
   9.250   0.9268   0.02552   0.02013   0.0146   0.0151   1.0000
   9.500   0.9424   0.02722   0.02206   0.0161   0.0147   1.0000
   9.750   0.9552   0.02927   0.02439   0.0179   0.0143   1.0000
  10.000   0.9635   0.03184   0.02729   0.0199   0.0141   1.0000
  10.250   0.9652   0.03507   0.03087   0.0223   0.0140   1.0000
  10.500   0.9585   0.03891   0.03508   0.0252   0.0140   1.0000
  10.750   0.9471   0.04230   0.03877   0.0282   0.0140   1.0000
  11.000   0.9302   0.04517   0.04185   0.0315   0.0138   1.0000
  11.250   0.9030   0.04961   0.04653   0.0328   0.0140   1.0000
  11.500   0.8802   0.05444   0.05155   0.0316   0.0142   1.0000
  11.750   0.8560   0.06054   0.05782   0.0279   0.0144   1.0000
  12.000   0.8260   0.06911   0.06655   0.0215   0.0145   1.0000
  12.250   0.8037   0.07764   0.07518   0.0148   0.0149   1.0000
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