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Eiffel 430 (Lachassgne) (eiffel430-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Eiffel 430 (Lachassgne) (eiffel430-il)
Reynolds number: 50,000
Max Cl/Cd: 36.41 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eiffel430-il-50000.txt
Download as CSV file: xf-eiffel430-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Eiffel 430 (Lachassgne)                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2956   0.10983   0.10324  -0.0275   1.0000   0.1839
  -9.750  -0.3068   0.10928   0.10283  -0.0276   1.0000   0.1873
  -9.500  -0.3325   0.11031   0.10407  -0.0274   1.0000   0.1885
  -9.250  -0.3039   0.10359   0.09735  -0.0259   1.0000   0.1923
  -9.000  -0.3020   0.10116   0.09502  -0.0245   1.0000   0.1963
  -8.750  -0.3126   0.09999   0.09399  -0.0228   1.0000   0.1999
  -8.500  -0.3381   0.10019   0.09440  -0.0202   1.0000   0.2020
  -8.250  -0.3700   0.10099   0.09541  -0.0172   1.0000   0.2030
  -8.000  -0.4023   0.10202   0.09665  -0.0140   1.0000   0.2034
  -7.750  -0.3990   0.09850   0.09325  -0.0114   0.9979   0.2052
  -7.500  -0.3632   0.09336   0.08806  -0.0153   0.9880   0.2125
  -7.250  -0.3383   0.08945   0.08410  -0.0262   0.9705   0.2201
  -7.000  -0.3096   0.08514   0.07976  -0.0287   0.9597   0.2288
  -6.750  -0.2866   0.08127   0.07584  -0.0342   0.9465   0.2379
  -6.500  -0.2644   0.07810   0.07258  -0.0407   0.9334   0.2508
  -6.250  -0.2401   0.07528   0.06965  -0.0462   0.9219   0.2658
  -6.000  -0.2184   0.07093   0.06535  -0.0446   0.9132   0.2731
  -5.750  -0.1927   0.06746   0.06183  -0.0480   0.9050   0.2890
  -5.500  -0.1789   0.06491   0.05924  -0.0487   0.8938   0.3055
  -5.250  -0.1550   0.06217   0.05642  -0.0514   0.8868   0.3375
  -5.000  -0.1463   0.05961   0.05392  -0.0481   0.8767   0.3601
  -4.250  -0.1137   0.05237   0.04685  -0.0374   0.8544   0.4908
  -4.000  -0.1031   0.05000   0.04451  -0.0343   0.8469   0.5255
  -3.750  -0.0944   0.04797   0.04246  -0.0323   0.8387   0.5458
  -3.500  -0.0676   0.04559   0.03992  -0.0361   0.8335   0.5525
  -3.250   0.0402   0.04274   0.03512  -0.0656   0.8231   0.2567
  -3.000   0.0810   0.04011   0.03175  -0.0679   0.8183   0.2137
  -2.750   0.1053   0.03852   0.02984  -0.0673   0.8128   0.2139
  -2.500   0.1250   0.03736   0.02836  -0.0659   0.8060   0.2157
  -2.250   0.1582   0.03568   0.02621  -0.0662   0.8011   0.2189
  -2.000   0.1814   0.03428   0.02472  -0.0651   0.7940   0.2300
  -1.750   0.2077   0.03291   0.02315  -0.0644   0.7874   0.2426
  -1.500   0.2459   0.03107   0.02102  -0.0653   0.7826   0.2676
  -1.250   0.2705   0.02996   0.01984  -0.0646   0.7756   0.2947
  -1.000   0.3143   0.02860   0.01839  -0.0669   0.7696   0.3393
  -0.750   0.3639   0.02724   0.01708  -0.0700   0.7650   0.3897
  -0.500   0.3931   0.02676   0.01672  -0.0701   0.7565   0.4119
  -0.250   0.4306   0.02588   0.01607  -0.0713   0.7505   0.4484
   0.000   0.5437   0.02337   0.01498  -0.0866   0.7437   1.0000
   0.250   0.5725   0.02343   0.01476  -0.0860   0.7338   1.0000
   0.500   0.5992   0.02351   0.01461  -0.0850   0.7228   1.0000
   0.750   0.6333   0.02331   0.01418  -0.0850   0.7130   1.0000
   1.000   0.6578   0.02335   0.01407  -0.0835   0.6980   1.0000
   1.250   0.6834   0.02340   0.01398  -0.0823   0.6829   1.0000
   1.500   0.7099   0.02348   0.01393  -0.0812   0.6675   1.0000
   1.750   0.7365   0.02360   0.01393  -0.0802   0.6509   1.0000
   2.000   0.7625   0.02380   0.01402  -0.0792   0.6331   1.0000
   2.250   0.7875   0.02411   0.01423  -0.0781   0.6143   1.0000
   2.500   0.8115   0.02454   0.01455  -0.0769   0.5957   1.0000
   2.750   0.8343   0.02502   0.01495  -0.0757   0.5772   1.0000
   3.000   0.8560   0.02552   0.01539  -0.0743   0.5598   1.0000
   3.250   0.8773   0.02601   0.01581  -0.0729   0.5439   1.0000
   3.500   0.8996   0.02644   0.01617  -0.0716   0.5299   1.0000
   3.750   0.9221   0.02679   0.01646  -0.0704   0.5167   1.0000
   4.000   0.9393   0.02742   0.01714  -0.0686   0.5030   1.0000
   4.250   0.9579   0.02794   0.01767  -0.0669   0.4902   1.0000
   4.500   0.9783   0.02830   0.01801  -0.0654   0.4780   1.0000
   4.750   1.0006   0.02850   0.01817  -0.0640   0.4661   1.0000
   5.000   1.0191   0.02889   0.01858  -0.0623   0.4530   1.0000
   5.250   1.0384   0.02933   0.01902  -0.0606   0.4406   1.0000
   5.500   1.0600   0.02962   0.01924  -0.0592   0.4273   1.0000
   5.750   1.0840   0.02997   0.01948  -0.0580   0.4132   1.0000
   6.000   1.1131   0.03057   0.01981  -0.0577   0.3970   1.0000
   6.250   1.1472   0.03210   0.02098  -0.0584   0.3762   1.0000
   6.500   1.1820   0.03522   0.02376  -0.0599   0.3512   1.0000
   6.750   1.2010   0.03894   0.02750  -0.0591   0.3312   1.0000
   7.000   1.2119   0.04234   0.03107  -0.0571   0.3147   1.0000
   7.250   1.2217   0.04560   0.03449  -0.0551   0.3011   1.0000
   7.500   1.2331   0.04883   0.03783  -0.0533   0.2893   1.0000
   7.750   1.2264   0.05130   0.04077  -0.0490   0.2807   1.0000
   8.000   1.2301   0.05436   0.04402  -0.0465   0.2726   1.0000
   8.250   1.2216   0.05720   0.04720  -0.0426   0.2660   1.0000
   8.500   1.2285   0.06024   0.05032  -0.0407   0.2586   1.0000
   8.750   1.2027   0.06368   0.05414  -0.0356   0.2553   1.0000
   9.000   1.1769   0.06747   0.05818  -0.0312   0.2521   1.0000
   9.250   1.1426   0.07180   0.06268  -0.0268   0.2507   1.0000
   9.500   0.9764   0.08852   0.07955  -0.0258   0.2662   1.0000
   9.750   0.9914   0.09094   0.08199  -0.0245   0.2586   1.0000
  10.000   0.9502   0.10188   0.09293  -0.0283   0.2602   1.0000
  10.250   0.7477   0.13861   0.12956  -0.0564   0.4119   1.0000
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