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Eiffel 430 (Lachassgne) (eiffel430-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Eiffel 430 (Lachassgne) (eiffel430-il)
Reynolds number: 100,000
Max Cl/Cd: 47.2 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eiffel430-il-100000.txt
Download as CSV file: xf-eiffel430-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2947   0.10116   0.09667  -0.0305   1.0000   0.1098
  -9.500  -0.3031   0.09982   0.09545  -0.0303   1.0000   0.1125
  -9.250  -0.3284   0.10023   0.09601  -0.0321   0.9970   0.1142
  -9.000  -0.3170   0.09562   0.09142  -0.0410   0.9782   0.1155
  -8.750  -0.2758   0.08956   0.08533  -0.0394   0.9715   0.1178
  -8.500  -0.2493   0.08552   0.08127  -0.0431   0.9557   0.1213
  -8.250  -0.2293   0.08182   0.07753  -0.0504   0.9365   0.1264
  -8.000  -0.2169   0.07809   0.07369  -0.0630   0.9114   0.1301
  -7.750  -0.1858   0.07361   0.06919  -0.0612   0.8953   0.1330
  -7.500  -0.1640   0.07046   0.06596  -0.0638   0.8712   0.1377
  -7.250  -0.1595   0.06871   0.06392  -0.0731   0.8369   0.1443
  -7.000  -0.1414   0.06455   0.05978  -0.0709   0.8097   0.1457
  -6.750  -0.1238   0.06167   0.05679  -0.0701   0.7820   0.1483
  -6.500  -0.1082   0.05927   0.05422  -0.0707   0.7573   0.1532
  -6.250  -0.0949   0.05700   0.05159  -0.0749   0.7381   0.1596
  -6.000  -0.0786   0.05401   0.04854  -0.0733   0.7226   0.1618
  -5.750  -0.0615   0.05189   0.04628  -0.0728   0.7074   0.1674
  -5.500  -0.0436   0.04974   0.04380  -0.0749   0.6964   0.1752
  -5.250  -0.0266   0.04721   0.04124  -0.0737   0.6859   0.1784
  -4.500   0.0370   0.03584   0.02854  -0.0763   0.6633   0.1311
  -4.250   0.0585   0.03336   0.02580  -0.0755   0.6568   0.1253
  -4.000   0.0795   0.03076   0.02288  -0.0746   0.6505   0.1220
  -3.750   0.1003   0.02641   0.01766  -0.0732   0.6454   0.1164
  -3.500   0.1246   0.02524   0.01634  -0.0723   0.6401   0.1184
  -3.250   0.1487   0.02441   0.01539  -0.0714   0.6330   0.1229
  -3.000   0.1740   0.02282   0.01334  -0.0704   0.6275   0.1282
  -2.750   0.1997   0.02194   0.01233  -0.0697   0.6223   0.1328
  -2.500   0.2255   0.02136   0.01166  -0.0689   0.6167   0.1408
  -2.250   0.2510   0.02101   0.01128  -0.0681   0.6112   0.1507
  -2.000   0.2774   0.02053   0.01065  -0.0673   0.6063   0.1639
  -1.750   0.3026   0.02024   0.01027  -0.0663   0.6011   0.1864
  -1.500   0.3273   0.01967   0.00968  -0.0655   0.5946   0.2111
  -1.250   0.3527   0.01929   0.00913  -0.0647   0.5880   0.2338
  -1.000   0.3786   0.01866   0.00858  -0.0642   0.5813   0.2517
  -0.750   0.4048   0.01814   0.00816  -0.0639   0.5744   0.2714
  -0.500   0.4320   0.01770   0.00776  -0.0636   0.5685   0.2903
  -0.250   0.4599   0.01730   0.00745  -0.0634   0.5617   0.3036
   0.000   0.4904   0.01700   0.00718  -0.0637   0.5535   0.3170
   0.250   0.5221   0.01668   0.00697  -0.0643   0.5455   0.3334
   0.500   0.5504   0.01644   0.00683  -0.0642   0.5369   0.3509
   0.750   0.5765   0.01622   0.00677  -0.0637   0.5281   0.3749
   1.000   0.6942   0.01493   0.00684  -0.0825   0.4917   1.0000
   1.250   0.7148   0.01515   0.00674  -0.0808   0.4279   1.0000
   1.500   0.7309   0.01564   0.00668  -0.0784   0.4012   1.0000
   1.750   0.7500   0.01612   0.00686  -0.0766   0.3914   1.0000
   2.000   0.7703   0.01656   0.00712  -0.0751   0.3855   1.0000
   2.250   0.7917   0.01698   0.00739  -0.0738   0.3820   1.0000
   2.500   0.8140   0.01738   0.00765  -0.0727   0.3795   1.0000
   2.750   0.8373   0.01777   0.00796  -0.0717   0.3766   1.0000
   3.000   0.8609   0.01824   0.00834  -0.0709   0.3725   1.0000
   3.250   0.8861   0.01883   0.00876  -0.0704   0.3680   1.0000
   3.500   0.9143   0.01951   0.00924  -0.0705   0.3641   1.0000
   3.750   0.9396   0.02002   0.00976  -0.0701   0.3600   1.0000
   4.000   0.9673   0.02076   0.01038  -0.0701   0.3544   1.0000
   4.250   0.9988   0.02183   0.01125  -0.0710   0.3486   1.0000
   4.500   1.0222   0.02243   0.01196  -0.0703   0.3438   1.0000
   4.750   1.0491   0.02341   0.01289  -0.0704   0.3374   1.0000
   5.000   1.0749   0.02455   0.01402  -0.0703   0.3305   1.0000
   5.250   1.0986   0.02566   0.01517  -0.0698   0.3221   1.0000
   5.500   1.1192   0.02686   0.01648  -0.0688   0.3131   1.0000
   5.750   1.1409   0.02840   0.01802  -0.0682   0.3023   1.0000
   6.000   1.1613   0.02986   0.01948  -0.0673   0.2903   1.0000
   6.250   1.1752   0.03061   0.02045  -0.0650   0.2778   1.0000
   6.500   1.1880   0.03140   0.02143  -0.0626   0.2647   1.0000
   6.750   1.2005   0.03208   0.02228  -0.0601   0.2520   1.0000
   7.000   1.2148   0.03257   0.02285  -0.0579   0.2412   1.0000
   7.250   1.2291   0.03271   0.02308  -0.0556   0.2313   1.0000
   7.500   1.2399   0.03307   0.02366  -0.0527   0.2207   1.0000
   7.750   1.2561   0.03283   0.02336  -0.0507   0.2150   1.0000
   8.000   1.2660   0.03325   0.02403  -0.0477   0.2049   1.0000
   8.250   1.2796   0.03294   0.02369  -0.0453   0.1999   1.0000
   8.500   1.2905   0.03342   0.02437  -0.0426   0.1914   1.0000
   8.750   1.3020   0.03316   0.02404  -0.0399   0.1872   1.0000
   9.000   1.3134   0.03404   0.02510  -0.0375   0.1799   1.0000
   9.250   1.3236   0.03415   0.02517  -0.0347   0.1755   1.0000
   9.500   1.3343   0.03496   0.02605  -0.0323   0.1704   1.0000
   9.750   1.3436   0.03576   0.02693  -0.0297   0.1654   1.0000
  10.000   1.3526   0.03621   0.02727  -0.0270   0.1615   1.0000
  10.250   1.3634   0.03762   0.02881  -0.0250   0.1572   1.0000
  10.500   1.3736   0.03899   0.03031  -0.0229   0.1532   1.0000
  10.750   1.3883   0.04009   0.03141  -0.0215   0.1499   1.0000
  11.000   1.4113   0.04169   0.03293  -0.0214   0.1465   1.0000
  11.250   1.4134   0.04378   0.03535  -0.0187   0.1441   1.0000
  11.500   1.4145   0.04589   0.03772  -0.0161   0.1416   1.0000
  11.750   1.4185   0.04781   0.03980  -0.0139   0.1390   1.0000
  12.000   1.4299   0.04957   0.04164  -0.0126   0.1365   1.0000
  12.250   1.4600   0.05214   0.04412  -0.0138   0.1336   1.0000
  12.500   1.4413   0.05496   0.04730  -0.0097   0.1329   1.0000
  12.750   1.4173   0.05841   0.05110  -0.0061   0.1322   1.0000
  13.000   1.3874   0.06267   0.05568  -0.0031   0.1318   1.0000
  13.250   1.3486   0.06820   0.06153  -0.0011   0.1317   1.0000
  13.500   1.2960   0.07605   0.06967  -0.0008   0.1322   1.0000
  13.750   1.2234   0.08811   0.08199  -0.0037   0.1332   1.0000
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