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RUTAN WING AIRFOIL (amsoil2-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RUTAN WING AIRFOIL (amsoil2-il)
Reynolds number: 50,000
Max Cl/Cd: 25.34 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-amsoil2-il-50000-n5.txt
Download as CSV file: xf-amsoil2-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RUTAN WING AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.6038   0.09792   0.08983  -0.0286   1.0000   0.0775
 -10.250  -0.6157   0.09052   0.08243  -0.0338   1.0000   0.0774
 -10.000  -0.6325   0.08367   0.07556  -0.0384   1.0000   0.0771
  -9.750  -0.6530   0.07774   0.06957  -0.0414   1.0000   0.0768
  -9.500  -0.6743   0.07279   0.06452  -0.0422   1.0000   0.0767
  -9.250  -0.6907   0.06797   0.05951  -0.0425   1.0000   0.0766
  -9.000  -0.7024   0.06342   0.05470  -0.0422   1.0000   0.0767
  -8.750  -0.7111   0.05902   0.04995  -0.0413   1.0000   0.0772
  -8.500  -0.7146   0.05511   0.04566  -0.0400   1.0000   0.0781
  -8.250  -0.7003   0.05333   0.04392  -0.0391   1.0000   0.0798
  -8.000  -0.6916   0.05100   0.04143  -0.0378   1.0000   0.0815
  -7.750  -0.6848   0.04838   0.03855  -0.0361   1.0000   0.0830
  -7.500  -0.6777   0.04573   0.03558  -0.0342   1.0000   0.0842
  -7.250  -0.6697   0.04326   0.03271  -0.0321   1.0000   0.0861
  -7.000  -0.6609   0.04088   0.02982  -0.0299   1.0000   0.0885
  -6.750  -0.6464   0.03943   0.02838  -0.0284   1.0000   0.0906
  -6.500  -0.6319   0.03796   0.02680  -0.0267   1.0000   0.0928
  -6.250  -0.6167   0.03639   0.02500  -0.0250   1.0000   0.0952
  -6.000  -0.6008   0.03489   0.02316  -0.0233   1.0000   0.0988
  -5.750  -0.5837   0.03357   0.02172  -0.0219   1.0000   0.1020
  -5.500  -0.5657   0.03249   0.02061  -0.0206   1.0000   0.1053
  -5.250  -0.5468   0.03142   0.01938  -0.0192   1.0000   0.1094
  -5.000  -0.5271   0.03041   0.01818  -0.0180   1.0000   0.1143
  -4.750  -0.5076   0.02955   0.01740  -0.0168   1.0000   0.1190
  -4.500  -0.4871   0.02879   0.01653  -0.0156   1.0000   0.1251
  -4.250  -0.4667   0.02804   0.01579  -0.0145   1.0000   0.1316
  -4.000  -0.4464   0.02743   0.01516  -0.0133   1.0000   0.1394
  -3.750  -0.4261   0.02681   0.01456  -0.0122   1.0000   0.1480
  -3.500  -0.4005   0.02626   0.01394  -0.0121   0.9980   0.1600
  -3.250  -0.3681   0.02559   0.01334  -0.0135   0.9936   0.1759
  -3.000  -0.3374   0.02488   0.01277  -0.0147   0.9886   0.1966
  -2.750  -0.3058   0.02410   0.01219  -0.0162   0.9839   0.2288
  -2.500  -0.2777   0.02291   0.01160  -0.0174   0.9787   0.3004
  -2.250  -0.2610   0.02155   0.01213  -0.0145   0.9742   0.6198
  -2.000  -0.2375   0.02190   0.01266  -0.0119   0.9689   0.7465
  -1.750  -0.2152   0.02230   0.01309  -0.0092   0.9625   0.8112
  -1.500  -0.1862   0.02275   0.01349  -0.0077   0.9580   0.8627
  -1.250  -0.1506   0.02317   0.01382  -0.0077   0.9541   0.9070
  -1.000  -0.0634   0.02387   0.01435  -0.0171   0.9575   0.9603
  -0.750   0.0162   0.02405   0.01438  -0.0274   0.9582   0.9847
  -0.500   0.0607   0.02406   0.01430  -0.0317   0.9532   0.9937
  -0.250   0.1010   0.02408   0.01426  -0.0353   0.9472   1.0000
   0.000   0.1318   0.02413   0.01426  -0.0370   0.9410   1.0000
   0.250   0.1512   0.02423   0.01434  -0.0366   0.9318   1.0000
   0.500   0.1838   0.02434   0.01443  -0.0385   0.9261   1.0000
   0.750   0.1975   0.02451   0.01460  -0.0370   0.9161   1.0000
   1.000   0.2289   0.02467   0.01478  -0.0385   0.9101   1.0000
   1.250   0.2412   0.02490   0.01502  -0.0365   0.9001   1.0000
   1.500   0.2704   0.02510   0.01526  -0.0375   0.8934   1.0000
   1.750   0.2827   0.02539   0.01558  -0.0354   0.8834   1.0000
   2.000   0.3149   0.02557   0.01582  -0.0366   0.8756   1.0000
   2.250   0.3443   0.02554   0.01586  -0.0366   0.8600   1.0000
   2.500   0.3953   0.02476   0.01518  -0.0386   0.8357   1.0000
   2.750   0.4256   0.02407   0.01458  -0.0371   0.8085   1.0000
   3.000   0.4583   0.02315   0.01372  -0.0356   0.7805   1.0000
   3.250   0.4823   0.02231   0.01293  -0.0326   0.7480   1.0000
   3.500   0.4999   0.02175   0.01240  -0.0291   0.7107   1.0000
   3.750   0.5151   0.02142   0.01213  -0.0257   0.6643   1.0000
   4.000   0.5330   0.02103   0.01166  -0.0223   0.5830   1.0000
   4.250   0.5473   0.02166   0.01065  -0.0175   0.3310   1.0000
   4.500   0.5540   0.02335   0.01156  -0.0147   0.2479   1.0000
   4.750   0.5674   0.02461   0.01246  -0.0128   0.2132   1.0000
   5.000   0.5837   0.02571   0.01334  -0.0113   0.1914   1.0000
   5.250   0.6024   0.02673   0.01420  -0.0101   0.1752   1.0000
   5.500   0.6235   0.02766   0.01509  -0.0091   0.1615   1.0000
   5.750   0.6474   0.02859   0.01601  -0.0084   0.1502   1.0000
   6.000   0.6731   0.02958   0.01691  -0.0081   0.1408   1.0000
   6.250   0.7011   0.03053   0.01791  -0.0079   0.1320   1.0000
   6.500   0.7300   0.03163   0.01898  -0.0079   0.1248   1.0000
   6.750   0.7585   0.03276   0.02018  -0.0079   0.1182   1.0000
   7.000   0.7865   0.03407   0.02141  -0.0080   0.1129   1.0000
   7.250   0.8131   0.03547   0.02304  -0.0077   0.1074   1.0000
   7.500   0.8387   0.03691   0.02453  -0.0075   0.1033   1.0000
   7.750   0.8631   0.03856   0.02626  -0.0073   0.0995   1.0000
   8.000   0.8851   0.04041   0.02846  -0.0066   0.0956   1.0000
   8.250   0.9068   0.04228   0.03052  -0.0060   0.0926   1.0000
   8.500   0.9282   0.04402   0.03229  -0.0056   0.0898   1.0000
   8.750   0.9438   0.04645   0.03510  -0.0044   0.0871   1.0000
   9.000   0.9566   0.04915   0.03823  -0.0031   0.0848   1.0000
   9.250   0.9681   0.05183   0.04124  -0.0018   0.0828   1.0000
   9.500   0.9801   0.05418   0.04379  -0.0007   0.0809   1.0000
   9.750   0.9955   0.05623   0.04587   0.0001   0.0790   1.0000
  10.000   0.9945   0.05968   0.04973   0.0020   0.0776   1.0000
  10.250   0.9860   0.06358   0.05407   0.0042   0.0767   1.0000
  10.500   0.9736   0.06760   0.05846   0.0063   0.0762   1.0000
  10.750   0.9539   0.07166   0.06280   0.0085   0.0759   1.0000
  11.000   0.9287   0.07626   0.06764   0.0097   0.0758   1.0000
  11.250   0.8993   0.08190   0.07349   0.0092   0.0760   1.0000
  11.500   0.8665   0.08898   0.08074   0.0065   0.0763   1.0000
  11.750   0.8330   0.09783   0.08970   0.0015   0.0768   1.0000
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