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Eiffel 385 (S.T. Ae) (eiffel385-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Eiffel 385 (S.T. Ae) (eiffel385-il)
Reynolds number: 100,000
Max Cl/Cd: 52.46 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eiffel385-il-100000.txt
Download as CSV file: xf-eiffel385-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Eiffel 385 (S.T. Ae)                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3108   0.09951   0.09446  -0.0292   1.0000   0.1697
 -11.000  -0.3427   0.09903   0.09413  -0.0279   1.0000   0.1732
 -10.750  -0.4586   0.08861   0.08393  -0.0325   1.0000   0.1325
 -10.500  -0.4599   0.08677   0.08216  -0.0291   1.0000   0.1333
 -10.250  -0.4656   0.08536   0.08081  -0.0262   1.0000   0.1339
 -10.000  -0.4502   0.08327   0.07873  -0.0266   0.9967   0.1357
  -9.750  -0.4438   0.06800   0.06330  -0.0475   0.9832   0.1262
  -9.500  -0.4538   0.03962   0.03359  -0.0782   0.9694   0.1358
  -9.250  -0.4217   0.03689   0.03042  -0.0817   0.9590   0.1473
  -9.000  -0.3767   0.03980   0.03372  -0.0819   0.9505   0.1540
  -8.750  -0.3383   0.03867   0.03240  -0.0849   0.9418   0.1648
  -8.500  -0.3077   0.03663   0.02996  -0.0875   0.9313   0.1767
  -8.250  -0.2633   0.03741   0.03084  -0.0895   0.9249   0.1866
  -8.000  -0.2344   0.03705   0.03044  -0.0900   0.9142   0.1950
  -7.750  -0.1940   0.03479   0.02763  -0.0941   0.9081   0.2075
  -7.500  -0.1660   0.03519   0.02831  -0.0933   0.8977   0.2125
  -7.250  -0.1260   0.03329   0.02603  -0.0966   0.8920   0.2209
  -7.000  -0.0985   0.03172   0.02419  -0.0975   0.8828   0.2265
  -6.750  -0.0608   0.03098   0.02345  -0.0991   0.8763   0.2318
  -6.500  -0.0152   0.02925   0.02123  -0.1028   0.8727   0.2406
  -6.250   0.0052   0.02851   0.02045  -0.1018   0.8617   0.2449
  -6.000   0.0485   0.02766   0.01954  -0.1043   0.8572   0.2522
  -5.750   0.0811   0.02671   0.01831  -0.1052   0.8502   0.2612
  -5.500   0.1109   0.02629   0.01794  -0.1054   0.8420   0.2684
  -5.250   0.1538   0.02525   0.01669  -0.1078   0.8379   0.2797
  -5.000   0.1745   0.02517   0.01665  -0.1064   0.8276   0.2874
  -4.750   0.2128   0.02456   0.01596  -0.1078   0.8221   0.2998
  -4.500   0.2433   0.02430   0.01558  -0.1080   0.8146   0.3116
  -4.250   0.2721   0.02402   0.01535  -0.1078   0.8064   0.3204
  -4.000   0.3144   0.02337   0.01455  -0.1098   0.8019   0.3321
  -3.750   0.3326   0.02345   0.01470  -0.1079   0.7907   0.3394
  -3.500   0.3725   0.02289   0.01402  -0.1094   0.7852   0.3507
  -3.250   0.3932   0.02293   0.01410  -0.1080   0.7747   0.3586
  -3.000   0.4302   0.02245   0.01356  -0.1090   0.7683   0.3700
  -2.750   0.4527   0.02251   0.01362  -0.1079   0.7585   0.3806
  -2.500   0.4866   0.02210   0.01322  -0.1085   0.7514   0.3917
  -2.250   0.5113   0.02209   0.01316  -0.1077   0.7422   0.4016
  -2.000   0.5432   0.02171   0.01282  -0.1080   0.7343   0.4109
  -1.750   0.5695   0.02164   0.01274  -0.1075   0.7255   0.4201
  -1.500   0.6006   0.02135   0.01247  -0.1077   0.7170   0.4320
  -1.250   0.6269   0.02123   0.01244  -0.1073   0.7079   0.4463
  -1.000   0.6570   0.02093   0.01223  -0.1073   0.6992   0.4668
  -0.750   0.6842   0.02080   0.01226  -0.1070   0.6895   0.4941
  -0.500   0.7168   0.02030   0.01206  -0.1074   0.6808   0.5530
  -0.250   0.7679   0.01938   0.01210  -0.1116   0.6696   1.0000
   0.000   0.8020   0.01942   0.01189  -0.1123   0.6612   1.0000
   0.250   0.8219   0.01987   0.01230  -0.1108   0.6493   1.0000
   0.500   0.8522   0.02002   0.01230  -0.1108   0.6402   1.0000
   0.750   0.8750   0.02036   0.01260  -0.1098   0.6287   1.0000
   1.000   0.8989   0.02073   0.01292  -0.1089   0.6180   1.0000
   1.250   0.9284   0.02089   0.01297  -0.1089   0.6080   1.0000
   1.500   0.9480   0.02136   0.01346  -0.1074   0.5959   1.0000
   1.750   0.9781   0.02155   0.01354  -0.1075   0.5866   1.0000
   2.000   0.9983   0.02196   0.01399  -0.1061   0.5746   1.0000
   2.250   1.0210   0.02235   0.01438  -0.1051   0.5636   1.0000
   2.500   1.0496   0.02251   0.01446  -0.1050   0.5539   1.0000
   2.750   1.0678   0.02303   0.01506  -0.1034   0.5423   1.0000
   3.000   1.0983   0.02319   0.01512  -0.1036   0.5338   1.0000
   3.250   1.1162   0.02363   0.01566  -0.1019   0.5220   1.0000
   3.500   1.1387   0.02391   0.01595  -0.1009   0.5112   1.0000
   3.750   1.1676   0.02391   0.01586  -0.1008   0.5013   1.0000
   4.000   1.1847   0.02430   0.01634  -0.0990   0.4893   1.0000
   4.250   1.2086   0.02441   0.01643  -0.0982   0.4783   1.0000
   4.500   1.2350   0.02442   0.01637  -0.0977   0.4675   1.0000
   4.750   1.2514   0.02477   0.01680  -0.0958   0.4553   1.0000
   5.000   1.2721   0.02486   0.01688  -0.0944   0.4426   1.0000
   5.250   1.2948   0.02488   0.01682  -0.0934   0.4299   1.0000
   5.500   1.3144   0.02508   0.01702  -0.0920   0.4175   1.0000
   5.750   1.3290   0.02550   0.01753  -0.0899   0.4054   1.0000
   6.000   1.3477   0.02583   0.01786  -0.0885   0.3941   1.0000
   6.250   1.3688   0.02609   0.01806  -0.0874   0.3824   1.0000
   6.500   1.3789   0.02661   0.01872  -0.0847   0.3704   1.0000
   6.750   1.3918   0.02706   0.01923  -0.0824   0.3583   1.0000
   7.000   1.4048   0.02745   0.01962  -0.0802   0.3457   1.0000
   7.250   1.4142   0.02787   0.02003  -0.0774   0.3320   1.0000
   7.500   1.4123   0.02846   0.02075  -0.0728   0.3184   1.0000
   7.750   1.4102   0.02915   0.02150  -0.0685   0.3033   1.0000
   8.000   1.4052   0.03001   0.02240  -0.0641   0.2860   1.0000
   8.250   1.3971   0.03117   0.02353  -0.0598   0.2660   1.0000
   8.500   1.3831   0.03292   0.02533  -0.0555   0.2405   1.0000
   8.750   1.3661   0.03532   0.02758  -0.0517   0.2119   1.0000
   9.000   1.3500   0.03818   0.03020  -0.0487   0.1881   1.0000
   9.250   1.3383   0.04116   0.03304  -0.0465   0.1684   1.0000
   9.500   1.3312   0.04398   0.03572  -0.0448   0.1555   1.0000
   9.750   1.3281   0.04658   0.03815  -0.0434   0.1460   1.0000
  10.000   1.3307   0.04884   0.04044  -0.0423   0.1377   1.0000
  10.250   1.3375   0.05075   0.04217  -0.0412   0.1310   1.0000
  10.500   1.3443   0.05276   0.04427  -0.0403   0.1250   1.0000
  10.750   1.3638   0.05382   0.04506  -0.0394   0.1188   1.0000
  11.000   1.3699   0.05600   0.04746  -0.0387   0.1149   1.0000
  11.250   1.3806   0.05781   0.04929  -0.0380   0.1103   1.0000
  11.500   1.4074   0.05878   0.05010  -0.0375   0.1053   1.0000
  11.750   1.4083   0.06140   0.05296  -0.0369   0.1024   1.0000
  12.000   1.4157   0.06362   0.05529  -0.0364   0.0989   1.0000
  12.250   1.4511   0.06448   0.05592  -0.0362   0.0939   1.0000
  12.500   1.4433   0.06775   0.05949  -0.0356   0.0921   1.0000
  12.750   1.4402   0.07092   0.06291  -0.0352   0.0900   1.0000
  13.000   1.4386   0.07404   0.06622  -0.0350   0.0877   1.0000
  13.250   1.4767   0.07500   0.06691  -0.0348   0.0831   1.0000
  13.500   1.4579   0.07933   0.07157  -0.0347   0.0823   1.0000
  13.750   1.4387   0.08409   0.07666  -0.0350   0.0815   1.0000
  14.000   1.4194   0.08926   0.08213  -0.0358   0.0807   1.0000
  14.250   1.3970   0.09507   0.08823  -0.0371   0.0800   1.0000
  14.500   1.3717   0.10164   0.09508  -0.0392   0.0796   1.0000
  14.750   1.3407   0.10946   0.10320  -0.0421   0.0795   1.0000
  15.000   1.3004   0.11941   0.11346  -0.0467   0.0800   1.0000
  15.250   1.2489   0.13254   0.12689  -0.0536   0.0812   1.0000
  15.500   1.1900   0.14918   0.14373  -0.0627   0.0828   1.0000
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