Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

RAE 100 AIRFOIL (rae100-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: RAE 100 AIRFOIL (rae100-il)
Reynolds number: 1,000,000
Max Cl/Cd: 74.08 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae100-il-1000000.txt
Download as CSV file: xf-rae100-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 100 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
  ------ -------- --------- --------- -------- -------- --------
 -18.000  -0.9987   0.13801   0.13591   0.0213   1.0000   0.0103
 -17.750  -1.0351   0.12523   0.12298   0.0140   1.0000   0.0102
 -17.500  -1.0689   0.11379   0.11139   0.0075   1.0000   0.0101
 -17.250  -1.0954   0.10428   0.10176   0.0022   1.0000   0.0100
 -17.000  -1.1184   0.09570   0.09306  -0.0027   1.0000   0.0101
 -16.750  -1.1472   0.08641   0.08365  -0.0079   1.0000   0.0100
 -16.500  -1.1692   0.07866   0.07578  -0.0123   1.0000   0.0101
 -16.250  -1.1972   0.07022   0.06719  -0.0171   1.0000   0.0100
 -16.000  -1.2155   0.06336   0.06020  -0.0212   1.0000   0.0101
 -15.750  -1.2304   0.05725   0.05396  -0.0248   1.0000   0.0101
 -15.500  -1.2450   0.05134   0.04790  -0.0284   1.0000   0.0101
 -15.250  -1.2542   0.04647   0.04290  -0.0312   1.0000   0.0102
 -15.000  -1.2593   0.04243   0.03873  -0.0334   1.0000   0.0103
 -14.750  -1.2672   0.03844   0.03460  -0.0351   1.0000   0.0103
 -14.500  -1.2704   0.03538   0.03140  -0.0359   1.0000   0.0104
 -14.250  -1.2698   0.03306   0.02897  -0.0360   1.0000   0.0106
 -14.000  -1.2699   0.03098   0.02677  -0.0353   1.0000   0.0107
 -13.750  -1.2672   0.02939   0.02507  -0.0341   1.0000   0.0108
 -13.500  -1.2628   0.02808   0.02366  -0.0325   1.0000   0.0109
 -13.250  -1.2691   0.02629   0.02173  -0.0292   1.0000   0.0111
 -13.000  -1.2741   0.02471   0.02003  -0.0253   1.0000   0.0113
 -12.750  -1.2657   0.02356   0.01882  -0.0232   1.0000   0.0117
 -12.500  -1.2518   0.02270   0.01789  -0.0216   1.0000   0.0120
 -12.250  -1.2350   0.02200   0.01714  -0.0204   1.0000   0.0123
 -12.000  -1.2181   0.02125   0.01632  -0.0191   1.0000   0.0127
 -11.750  -1.2001   0.02055   0.01555  -0.0179   1.0000   0.0131
 -11.500  -1.1816   0.01984   0.01477  -0.0167   1.0000   0.0134
 -11.250  -1.1618   0.01923   0.01407  -0.0157   1.0000   0.0137
 -11.000  -1.1405   0.01875   0.01353  -0.0148   1.0000   0.0139
 -10.750  -1.1267   0.01744   0.01210  -0.0130   1.0000   0.0146
 -10.500  -1.1067   0.01674   0.01137  -0.0119   1.0000   0.0153
 -10.250  -1.0848   0.01624   0.01083  -0.0111   1.0000   0.0159
 -10.000  -1.0626   0.01575   0.01030  -0.0102   1.0000   0.0165
  -9.750  -1.0400   0.01530   0.00980  -0.0094   1.0000   0.0171
  -9.500  -1.0163   0.01497   0.00941  -0.0087   1.0000   0.0176
  -9.250  -0.9969   0.01412   0.00851  -0.0075   1.0000   0.0189
  -9.000  -0.9739   0.01369   0.00807  -0.0066   1.0000   0.0199
  -8.750  -0.9506   0.01331   0.00766  -0.0059   1.0000   0.0209
  -8.500  -0.9268   0.01298   0.00728  -0.0051   1.0000   0.0218
  -8.250  -0.9050   0.01242   0.00668  -0.0040   1.0000   0.0233
  -8.000  -0.8818   0.01202   0.00628  -0.0032   1.0000   0.0250
  -7.750  -0.8580   0.01172   0.00596  -0.0024   1.0000   0.0266
  -7.500  -0.8348   0.01135   0.00557  -0.0015   1.0000   0.0285
  -7.250  -0.8117   0.01096   0.00519  -0.0006   1.0000   0.0312
  -7.000  -0.7877   0.01070   0.00491   0.0002   1.0000   0.0333
  -6.750  -0.7647   0.01033   0.00454   0.0012   1.0000   0.0370
  -6.500  -0.7411   0.01005   0.00427   0.0021   1.0000   0.0406
  -6.250  -0.7179   0.00973   0.00397   0.0030   1.0000   0.0458
  -6.000  -0.6943   0.00949   0.00374   0.0040   1.0000   0.0504
  -5.750  -0.6715   0.00917   0.00348   0.0050   1.0000   0.0585
  -5.500  -0.6485   0.00890   0.00324   0.0060   1.0000   0.0675
  -5.250  -0.6257   0.00864   0.00304   0.0070   1.0000   0.0781
  -5.000  -0.6032   0.00839   0.00284   0.0081   1.0000   0.0907
  -4.750  -0.5727   0.00810   0.00264   0.0074   0.9987   0.1088
  -4.500  -0.5364   0.00781   0.00246   0.0055   0.9959   0.1311
  -4.250  -0.5007   0.00752   0.00229   0.0038   0.9926   0.1570
  -4.000  -0.4661   0.00722   0.00211   0.0023   0.9882   0.1852
  -3.750  -0.4299   0.00693   0.00196   0.0004   0.9843   0.2161
  -3.500  -0.3960   0.00666   0.00182  -0.0009   0.9781   0.2479
  -3.250  -0.3598   0.00639   0.00168  -0.0027   0.9714   0.2822
  -3.000  -0.3254   0.00615   0.00156  -0.0041   0.9603   0.3147
  -2.750  -0.2911   0.00594   0.00145  -0.0054   0.9448   0.3470
  -2.500  -0.2606   0.00577   0.00134  -0.0058   0.9218   0.3777
  -2.250  -0.2336   0.00565   0.00125  -0.0053   0.8934   0.4068
  -2.000  -0.2080   0.00558   0.00117  -0.0046   0.8626   0.4345
  -1.750  -0.1826   0.00554   0.00111  -0.0039   0.8323   0.4614
  -1.500  -0.1568   0.00550   0.00106  -0.0032   0.8031   0.4887
  -1.250  -0.1311   0.00546   0.00101  -0.0026   0.7748   0.5162
  -1.000  -0.1051   0.00543   0.00098  -0.0020   0.7483   0.5422
  -0.750  -0.0790   0.00542   0.00095  -0.0015   0.7220   0.5681
  -0.500  -0.0526   0.00540   0.00094  -0.0010   0.6962   0.5942
  -0.250  -0.0264   0.00539   0.00092  -0.0005   0.6711   0.6196
   0.000   0.0000   0.00540   0.00092   0.0000   0.6450   0.6450
   0.250   0.0263   0.00539   0.00092   0.0005   0.6191   0.6710
   0.500   0.0526   0.00540   0.00094   0.0010   0.5942   0.6962
   0.750   0.0789   0.00542   0.00095   0.0015   0.5682   0.7220
   1.000   0.1050   0.00544   0.00098   0.0020   0.5419   0.7483
   1.250   0.1310   0.00546   0.00101   0.0026   0.5159   0.7749
   1.500   0.1568   0.00550   0.00106   0.0032   0.4886   0.8031
   2.000   0.2080   0.00558   0.00117   0.0046   0.4351   0.8627
   2.250   0.2336   0.00565   0.00125   0.0053   0.4067   0.8934
   2.500   0.2605   0.00577   0.00134   0.0058   0.3776   0.9219
   2.750   0.2911   0.00593   0.00145   0.0054   0.3472   0.9448
   3.000   0.3254   0.00615   0.00156   0.0041   0.3148   0.9603
   3.250   0.3597   0.00639   0.00168   0.0027   0.2820   0.9714
   3.500   0.3959   0.00665   0.00182   0.0009   0.2486   0.9780
   3.750   0.4297   0.00693   0.00196  -0.0004   0.2163   0.9842
   4.000   0.4660   0.00722   0.00211  -0.0022   0.1853   0.9881
   4.250   0.5006   0.00752   0.00229  -0.0038   0.1568   0.9926
   4.500   0.5363   0.00781   0.00246  -0.0055   0.1313   0.9958
   4.750   0.5726   0.00810   0.00264  -0.0074   0.1087   0.9987
   5.000   0.6035   0.00839   0.00284  -0.0082   0.0904   1.0000
   5.250   0.6260   0.00865   0.00304  -0.0071   0.0779   1.0000
   5.500   0.6489   0.00890   0.00325  -0.0061   0.0676   1.0000
   5.750   0.6718   0.00918   0.00348  -0.0050   0.0585   1.0000
   6.000   0.6946   0.00949   0.00374  -0.0040   0.0504   1.0000
   6.250   0.7182   0.00973   0.00398  -0.0031   0.0458   1.0000
   6.500   0.7413   0.01006   0.00428  -0.0021   0.0407   1.0000
   6.750   0.7649   0.01033   0.00454  -0.0013   0.0369   1.0000
   7.000   0.7879   0.01070   0.00491  -0.0003   0.0333   1.0000
   7.250   0.8119   0.01096   0.00519   0.0005   0.0311   1.0000
   7.500   0.8349   0.01136   0.00557   0.0015   0.0284   1.0000
   7.750   0.8581   0.01173   0.00597   0.0024   0.0266   1.0000
   8.000   0.8820   0.01202   0.00628   0.0032   0.0250   1.0000
   8.250   0.9050   0.01242   0.00668   0.0040   0.0233   1.0000
   8.500   0.9268   0.01299   0.00729   0.0051   0.0218   1.0000
   8.750   0.9505   0.01332   0.00766   0.0059   0.0210   1.0000
   9.000   0.9738   0.01369   0.00807   0.0067   0.0199   1.0000
   9.250   0.9968   0.01411   0.00851   0.0075   0.0189   1.0000
   9.500   1.0161   0.01496   0.00940   0.0088   0.0176   1.0000
   9.750   1.0395   0.01532   0.00982   0.0095   0.0171   1.0000
  10.000   1.0622   0.01576   0.01031   0.0103   0.0165   1.0000
  10.250   1.0846   0.01622   0.01082   0.0111   0.0158   1.0000
  10.500   1.1062   0.01676   0.01139   0.0120   0.0153   1.0000
  10.750   1.1265   0.01741   0.01208   0.0130   0.0147   1.0000
  11.000   1.1405   0.01869   0.01347   0.0148   0.0139   1.0000
  11.250   1.1616   0.01921   0.01405   0.0157   0.0137   1.0000
  11.500   1.1805   0.01990   0.01483   0.0169   0.0135   1.0000
  11.750   1.1997   0.02053   0.01553   0.0180   0.0131   1.0000
  12.000   1.2180   0.02121   0.01628   0.0191   0.0126   1.0000
  12.250   1.2358   0.02187   0.01701   0.0203   0.0123   1.0000
  12.500   1.2520   0.02263   0.01782   0.0217   0.0119   1.0000
  12.750   1.2658   0.02350   0.01875   0.0232   0.0117   1.0000
  13.000   1.2733   0.02471   0.02004   0.0255   0.0113   1.0000
  13.250   1.2679   0.02632   0.02176   0.0294   0.0110   1.0000
  13.500   1.2612   0.02816   0.02375   0.0326   0.0109   1.0000
  13.750   1.2665   0.02940   0.02509   0.0342   0.0108   1.0000
  14.000   1.2706   0.03089   0.02667   0.0354   0.0107   1.0000
  14.250   1.2692   0.03308   0.02899   0.0360   0.0106   1.0000
  14.500   1.2686   0.03553   0.03155   0.0359   0.0105   1.0000
  14.750   1.2639   0.03879   0.03495   0.0350   0.0104   1.0000
  15.000   1.2586   0.04252   0.03883   0.0333   0.0103   1.0000
  15.250   1.2543   0.04646   0.04289   0.0312   0.0102   1.0000
  15.500   1.2456   0.05128   0.04784   0.0283   0.0101   1.0000
  15.750   1.2335   0.05682   0.05352   0.0250   0.0100   1.0000
  16.000   1.2156   0.06341   0.06025   0.0211   0.0100   1.0000
  16.250   1.1954   0.07057   0.06755   0.0168   0.0099   1.0000
  16.500   1.1749   0.07782   0.07492   0.0127   0.0100   1.0000
  16.750   1.1429   0.08713   0.08439   0.0074   0.0102   1.0000
  17.000   1.1205   0.09534   0.09271   0.0028   0.0101   1.0000
  17.250   1.0965   0.10409   0.10158  -0.0022   0.0101   1.0000
  17.500   1.0664   0.11442   0.11204  -0.0080   0.0101   1.0000
  17.750   1.0362   0.12520   0.12294  -0.0141   0.0101   1.0000
  18.000   0.9974   0.13855   0.13645  -0.0217   0.0103   1.0000
<< Back to RAE 100 AIRFOIL (rae100-il)

Polar data table (+)

Polar graphs


<< Back to RAE 100 AIRFOIL (rae100-il)