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

RAE 101 AIRFOIL (rae101-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: RAE 101 AIRFOIL (rae101-il)
Reynolds number: 1,000,000
Max Cl/Cd: 70.18 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae101-il-1000000-n5.txt
Download as CSV file: xf-rae101-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -1.0787   0.09699   0.09471  -0.0019   1.0000   0.0046
 -16.500  -1.1235   0.08363   0.08117  -0.0095   1.0000   0.0046
 -16.250  -1.1756   0.07008   0.06738  -0.0176   1.0000   0.0044
 -16.000  -1.1969   0.06265   0.05980  -0.0220   1.0000   0.0044
 -15.750  -1.2151   0.05605   0.05305  -0.0259   1.0000   0.0044
 -15.500  -1.2289   0.05046   0.04731  -0.0291   1.0000   0.0044
 -15.250  -1.2406   0.04551   0.04221  -0.0317   1.0000   0.0045
 -15.000  -1.2463   0.04171   0.03829  -0.0334   1.0000   0.0045
 -14.750  -1.2517   0.03826   0.03470  -0.0345   1.0000   0.0045
 -14.500  -1.2554   0.03533   0.03164  -0.0349   1.0000   0.0046
 -14.250  -1.2551   0.03309   0.02929  -0.0346   1.0000   0.0047
 -14.000  -1.2540   0.03116   0.02725  -0.0338   1.0000   0.0048
 -13.750  -1.2533   0.02941   0.02538  -0.0325   1.0000   0.0048
 -13.500  -1.2510   0.02796   0.02382  -0.0306   1.0000   0.0049
 -13.250  -1.2479   0.02669   0.02244  -0.0283   1.0000   0.0050
 -13.000  -1.2433   0.02562   0.02126  -0.0257   1.0000   0.0050
 -12.750  -1.2371   0.02463   0.02017  -0.0230   1.0000   0.0051
 -12.500  -1.2263   0.02364   0.01907  -0.0211   1.0000   0.0052
 -12.250  -1.2125   0.02276   0.01809  -0.0195   1.0000   0.0053
 -12.000  -1.1970   0.02196   0.01720  -0.0180   1.0000   0.0055
 -11.750  -1.1801   0.02122   0.01637  -0.0168   1.0000   0.0056
 -11.500  -1.1625   0.02050   0.01557  -0.0155   1.0000   0.0057
 -11.250  -1.1457   0.01966   0.01462  -0.0142   1.0000   0.0058
 -11.000  -1.1298   0.01866   0.01353  -0.0127   1.0000   0.0061
 -10.750  -1.1110   0.01793   0.01272  -0.0116   1.0000   0.0063
 -10.500  -1.0909   0.01731   0.01204  -0.0105   1.0000   0.0065
 -10.250  -1.0703   0.01674   0.01141  -0.0096   1.0000   0.0067
 -10.000  -1.0492   0.01620   0.01082  -0.0086   1.0000   0.0070
  -9.750  -1.0279   0.01567   0.01023  -0.0077   1.0000   0.0072
  -9.500  -1.0062   0.01518   0.00968  -0.0068   1.0000   0.0075
  -9.250  -0.9844   0.01470   0.00914  -0.0059   1.0000   0.0078
  -9.000  -0.9622   0.01426   0.00864  -0.0050   1.0000   0.0081
  -8.750  -0.9398   0.01385   0.00818  -0.0042   1.0000   0.0082
  -8.500  -0.9186   0.01329   0.00758  -0.0031   1.0000   0.0088
  -8.250  -0.8964   0.01287   0.00712  -0.0021   1.0000   0.0093
  -8.000  -0.8739   0.01249   0.00673  -0.0013   1.0000   0.0098
  -7.750  -0.8510   0.01216   0.00636  -0.0004   1.0000   0.0105
  -7.500  -0.8280   0.01184   0.00600   0.0005   1.0000   0.0111
  -7.250  -0.8049   0.01153   0.00567   0.0013   1.0000   0.0116
  -7.000  -0.7826   0.01115   0.00528   0.0023   1.0000   0.0128
  -6.750  -0.7599   0.01084   0.00497   0.0033   1.0000   0.0138
  -6.500  -0.7310   0.01055   0.00465   0.0029   0.9985   0.0149
  -6.250  -0.6987   0.01026   0.00434   0.0018   0.9948   0.0161
  -6.000  -0.6682   0.00994   0.00403   0.0010   0.9898   0.0186
  -5.750  -0.6356   0.00968   0.00376  -0.0002   0.9847   0.0206
  -5.500  -0.6027   0.00939   0.00348  -0.0014   0.9784   0.0240
  -5.250  -0.5676   0.00913   0.00323  -0.0031   0.9708   0.0275
  -5.000  -0.5329   0.00886   0.00298  -0.0047   0.9593   0.0339
  -4.750  -0.4978   0.00861   0.00274  -0.0064   0.9426   0.0412
  -4.500  -0.4675   0.00841   0.00252  -0.0069   0.9177   0.0506
  -4.250  -0.4413   0.00823   0.00231  -0.0065   0.8884   0.0641
  -4.000  -0.4163   0.00807   0.00213  -0.0059   0.8601   0.0801
  -3.750  -0.3916   0.00789   0.00194  -0.0052   0.8338   0.1032
  -3.500  -0.3669   0.00767   0.00176  -0.0046   0.8099   0.1344
  -3.250  -0.3422   0.00741   0.00158  -0.0040   0.7873   0.1758
  -3.000  -0.3175   0.00714   0.00141  -0.0035   0.7664   0.2219
  -2.750  -0.2931   0.00680   0.00124  -0.0029   0.7479   0.2844
  -2.500  -0.2679   0.00654   0.00113  -0.0025   0.7295   0.3405
  -2.250  -0.2419   0.00641   0.00104  -0.0021   0.7113   0.3737
  -2.000  -0.2154   0.00630   0.00097  -0.0018   0.6947   0.4022
  -1.500  -0.1620   0.00615   0.00087  -0.0013   0.6642   0.4513
  -1.250  -0.1352   0.00609   0.00083  -0.0011   0.6486   0.4741
  -1.000  -0.1083   0.00604   0.00080  -0.0008   0.6331   0.4966
  -0.750  -0.0813   0.00599   0.00078  -0.0006   0.6190   0.5179
  -0.500  -0.0542   0.00594   0.00076  -0.0004   0.6057   0.5394
  -0.250  -0.0271   0.00592   0.00075  -0.0002   0.5920   0.5590
   0.000   0.0000   0.00590   0.00075   0.0000   0.5764   0.5764
   0.250   0.0270   0.00592   0.00075   0.0002   0.5589   0.5920
   0.500   0.0542   0.00594   0.00076   0.0004   0.5394   0.6057
   0.750   0.0813   0.00599   0.00078   0.0006   0.5181   0.6190
   1.000   0.1083   0.00604   0.00080   0.0008   0.4965   0.6331
   1.250   0.1351   0.00609   0.00083   0.0011   0.4741   0.6487
   1.500   0.1620   0.00615   0.00087   0.0013   0.4515   0.6642
   2.000   0.2154   0.00631   0.00097   0.0018   0.4016   0.6947
   2.250   0.2418   0.00641   0.00104   0.0021   0.3734   0.7113
   2.500   0.2679   0.00654   0.00113   0.0025   0.3410   0.7298
   2.750   0.2931   0.00679   0.00124   0.0029   0.2855   0.7480
   3.000   0.3175   0.00714   0.00141   0.0035   0.2232   0.7665
   3.250   0.3422   0.00741   0.00158   0.0040   0.1764   0.7871
   3.500   0.3669   0.00767   0.00176   0.0046   0.1342   0.8094
   3.750   0.3917   0.00788   0.00194   0.0052   0.1046   0.8335
   4.000   0.4163   0.00807   0.00213   0.0059   0.0802   0.8600
   4.250   0.4413   0.00823   0.00231   0.0065   0.0643   0.8886
   4.500   0.4674   0.00841   0.00252   0.0069   0.0502   0.9175
   4.750   0.4977   0.00861   0.00274   0.0064   0.0413   0.9424
   5.000   0.5328   0.00886   0.00298   0.0047   0.0336   0.9592
   5.250   0.5678   0.00913   0.00323   0.0030   0.0275   0.9710
   5.500   0.6029   0.00940   0.00348   0.0013   0.0238   0.9787
   5.750   0.6357   0.00968   0.00376   0.0001   0.0206   0.9848
   6.000   0.6684   0.00994   0.00403  -0.0011   0.0186   0.9899
   6.250   0.6989   0.01027   0.00434  -0.0018   0.0161   0.9949
   6.500   0.7312   0.01055   0.00465  -0.0029   0.0149   0.9987
   6.750   0.7597   0.01084   0.00496  -0.0032   0.0138   1.0000
   7.000   0.7825   0.01115   0.00528  -0.0023   0.0128   1.0000
   7.250   0.8049   0.01152   0.00566  -0.0013   0.0117   1.0000
   7.500   0.8278   0.01185   0.00602  -0.0004   0.0111   1.0000
   7.750   0.8510   0.01215   0.00635   0.0004   0.0105   1.0000
   8.000   0.8738   0.01249   0.00673   0.0013   0.0099   1.0000
   8.250   0.8964   0.01287   0.00713   0.0022   0.0094   1.0000
   8.500   0.9186   0.01329   0.00757   0.0031   0.0088   1.0000
   8.750   0.9397   0.01386   0.00819   0.0042   0.0082   1.0000
   9.000   0.9622   0.01426   0.00865   0.0050   0.0081   1.0000
   9.250   0.9844   0.01471   0.00916   0.0059   0.0078   1.0000
   9.500   1.0063   0.01519   0.00970   0.0068   0.0076   1.0000
   9.750   1.0280   0.01568   0.01024   0.0077   0.0073   1.0000
  10.000   1.0494   0.01620   0.01082   0.0086   0.0070   1.0000
  10.250   1.0705   0.01675   0.01142   0.0095   0.0068   1.0000
  10.500   1.0912   0.01732   0.01204   0.0105   0.0065   1.0000
  10.750   1.1112   0.01795   0.01274   0.0115   0.0063   1.0000
  11.000   1.1305   0.01862   0.01349   0.0126   0.0061   1.0000
  11.250   1.1470   0.01956   0.01452   0.0140   0.0058   1.0000
  11.500   1.1625   0.02054   0.01560   0.0155   0.0057   1.0000
  11.750   1.1807   0.02120   0.01635   0.0167   0.0056   1.0000
  12.000   1.1981   0.02190   0.01713   0.0179   0.0055   1.0000
  12.250   1.2134   0.02272   0.01804   0.0193   0.0054   1.0000
  12.500   1.2273   0.02360   0.01902   0.0209   0.0052   1.0000
  12.750   1.2386   0.02458   0.02011   0.0228   0.0051   1.0000
  13.000   1.2451   0.02555   0.02119   0.0254   0.0051   1.0000
  13.250   1.2500   0.02661   0.02235   0.0280   0.0049   1.0000
  13.500   1.2530   0.02789   0.02374   0.0304   0.0049   1.0000
  13.750   1.2539   0.02943   0.02541   0.0323   0.0049   1.0000
  14.000   1.2548   0.03118   0.02727   0.0337   0.0048   1.0000
  14.250   1.2564   0.03308   0.02927   0.0345   0.0047   1.0000
  14.500   1.2569   0.03530   0.03161   0.0347   0.0046   1.0000
  14.750   1.2563   0.03789   0.03431   0.0344   0.0046   1.0000
  15.000   1.2495   0.04149   0.03806   0.0332   0.0045   1.0000
  15.250   1.2472   0.04484   0.04152   0.0318   0.0044   1.0000
  15.500   1.2333   0.05007   0.04692   0.0291   0.0045   1.0000
  15.750   1.2111   0.05697   0.05401   0.0251   0.0045   1.0000
  16.000   1.1957   0.06318   0.06034   0.0214   0.0045   1.0000
  16.250   1.1709   0.07127   0.06860   0.0165   0.0044   1.0000
<< Back to RAE 101 AIRFOIL (rae101-il)

Polar data table (+)

Polar graphs


<< Back to RAE 101 AIRFOIL (rae101-il)