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Eiffel 371 (Monge) (eiffel371-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Eiffel 371 (Monge) (eiffel371-il)
Reynolds number: 50,000
Max Cl/Cd: 19.9 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eiffel371-il-50000.txt
Download as CSV file: xf-eiffel371-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Eiffel 371 (Monge)                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3178   0.11211   0.10543  -0.0219   1.0000   0.2930
  -9.500  -0.3267   0.11016   0.10359  -0.0212   1.0000   0.3054
  -9.250  -0.3414   0.10901   0.10258  -0.0201   1.0000   0.3195
  -9.000  -0.3382   0.10638   0.10001  -0.0185   1.0000   0.3351
  -8.750  -0.3275   0.10319   0.09687  -0.0168   1.0000   0.3507
  -8.500  -0.3300   0.10099   0.09476  -0.0148   1.0000   0.3674
  -8.250  -0.3106   0.09700   0.09080  -0.0129   1.0000   0.3874
  -8.000  -0.3020   0.09413   0.08799  -0.0109   1.0000   0.4059
  -7.750  -0.2980   0.09153   0.08547  -0.0088   1.0000   0.4237
  -7.500  -0.2997   0.08920   0.08323  -0.0066   1.0000   0.4390
  -6.000  -0.5756   0.05990   0.05379  -0.0131   1.0000   0.1670
  -5.750  -0.5871   0.05517   0.04820  -0.0108   1.0000   0.1433
  -5.500  -0.5797   0.05226   0.04514  -0.0086   1.0000   0.1367
  -5.250  -0.5759   0.04929   0.04172  -0.0062   1.0000   0.1306
  -5.000  -0.5705   0.04748   0.03903  -0.0031   1.0000   0.1255
  -4.750  -0.5603   0.04542   0.03665  -0.0011   1.0000   0.1254
  -4.500  -0.5485   0.04358   0.03446   0.0009   1.0000   0.1256
  -4.250  -0.5350   0.04179   0.03233   0.0028   1.0000   0.1256
  -4.000  -0.5199   0.04009   0.03033   0.0045   1.0000   0.1259
  -3.750  -0.5039   0.03815   0.02836   0.0057   1.0000   0.1290
  -3.500  -0.4669   0.03696   0.02692   0.0037   0.9929   0.1367
  -3.250  -0.4187   0.03564   0.02530   0.0003   0.9828   0.1450
  -3.000  -0.3743   0.03451   0.02417  -0.0025   0.9723   0.1629
  -2.750  -0.3276   0.03346   0.02322  -0.0054   0.9625   0.1936
  -2.500  -0.0482   0.03316   0.02573  -0.0373   0.9723   1.0000
  -2.250  -0.0044   0.03338   0.02555  -0.0424   0.9576   1.0000
  -2.000   0.0355   0.03362   0.02548  -0.0464   0.9431   1.0000
  -1.750   0.0738   0.03389   0.02547  -0.0499   0.9285   1.0000
  -1.500   0.1107   0.03417   0.02550  -0.0529   0.9141   1.0000
  -1.250   0.1478   0.03443   0.02555  -0.0556   0.8996   1.0000
  -1.000   0.1854   0.03467   0.02558  -0.0582   0.8855   1.0000
  -0.750   0.2261   0.03485   0.02558  -0.0612   0.8718   1.0000
  -0.500   0.2791   0.03479   0.02534  -0.0659   0.8595   1.0000
  -0.250   0.3062   0.03509   0.02552  -0.0664   0.8450   1.0000
   0.000   0.3332   0.03540   0.02574  -0.0668   0.8308   1.0000
   0.250   0.3619   0.03570   0.02595  -0.0674   0.8169   1.0000
   0.500   0.3962   0.03586   0.02602  -0.0687   0.8033   1.0000
   0.750   0.4404   0.03574   0.02583  -0.0715   0.7906   1.0000
   1.000   0.5041   0.03491   0.02491  -0.0767   0.7798   1.0000
   1.250   0.5283   0.03516   0.02513  -0.0761   0.7650   1.0000
   1.500   0.5508   0.03551   0.02544  -0.0752   0.7504   1.0000
   1.750   0.5752   0.03578   0.02569  -0.0745   0.7358   1.0000
   2.000   0.5999   0.03605   0.02595  -0.0738   0.7213   1.0000
   2.250   0.6249   0.03634   0.02623  -0.0731   0.7073   1.0000
   2.500   0.6556   0.03636   0.02624  -0.0730   0.6937   1.0000
   2.750   0.7033   0.03562   0.02545  -0.0751   0.6818   1.0000
   3.000   0.7181   0.03633   0.02620  -0.0729   0.6671   1.0000
   3.250   0.7259   0.03739   0.02727  -0.0700   0.6523   1.0000
   3.500   0.7312   0.03861   0.02853  -0.0668   0.6381   1.0000
   3.750   0.7396   0.03971   0.02966  -0.0640   0.6248   1.0000
   4.000   0.7637   0.04008   0.03006  -0.0631   0.6129   1.0000
   4.250   0.7962   0.04002   0.03000  -0.0631   0.6012   1.0000
   4.500   0.7735   0.04257   0.03263  -0.0568   0.5881   1.0000
   4.750   0.7553   0.04491   0.03501  -0.0511   0.5762   1.0000
   5.000   0.8066   0.04397   0.03408  -0.0531   0.5658   1.0000
   5.250   0.7672   0.04719   0.03737  -0.0451   0.5545   1.0000
   5.500   0.6671   0.05268   0.04281  -0.0310   0.5458   1.0000
   5.750   0.7816   0.04903   0.03929  -0.0390   0.5328   1.0000
   6.000   0.6036   0.05922   0.04927  -0.0206   0.5253   1.0000
   6.250   0.6239   0.05982   0.04989  -0.0192   0.5147   1.0000
   6.500   0.7351   0.05419   0.04443  -0.0229   0.5006   1.0000
   6.750   0.6189   0.06376   0.05381  -0.0143   0.4906   1.0000
   7.000   0.6195   0.06568   0.05573  -0.0122   0.4782   1.0000
   7.250   0.6443   0.06576   0.05586  -0.0109   0.4655   1.0000
   7.500   0.7264   0.06072   0.05097  -0.0107   0.4542   1.0000
   7.750   0.6490   0.06990   0.06006  -0.0078   0.4418   1.0000
   8.000   0.6413   0.07310   0.06327  -0.0065   0.4302   1.0000
   8.250   0.6699   0.07317   0.06340  -0.0055   0.4195   1.0000
   8.500   0.6732   0.07553   0.06579  -0.0045   0.4082   1.0000
   8.750   0.6420   0.08152   0.07177  -0.0040   0.3978   1.0000
   9.000   0.6572   0.08301   0.07331  -0.0032   0.3871   1.0000
   9.250   0.6608   0.08581   0.07615  -0.0028   0.3776   1.0000
   9.500   0.6462   0.09100   0.08135  -0.0031   0.3717   1.0000
   9.750   0.6228   0.09731   0.08766  -0.0041   0.3694   1.0000
  10.000   0.6109   0.10277   0.09315  -0.0051   0.3702   1.0000
  10.250   0.6107   0.10751   0.09793  -0.0062   0.3730   1.0000
  10.500   0.6214   0.11169   0.10217  -0.0072   0.3749   1.0000
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