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Eiffel 371 (Monge) (eiffel371-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Eiffel 371 (Monge) (eiffel371-il)
Reynolds number: 500,000
Max Cl/Cd: 70.14 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eiffel371-il-500000.txt
Download as CSV file: xf-eiffel371-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3180   0.08748   0.08548  -0.0423   1.0000   0.0259
 -10.500  -0.3255   0.08412   0.08215  -0.0419   1.0000   0.0261
 -10.250  -0.3348   0.08065   0.07871  -0.0416   1.0000   0.0263
 -10.000  -0.3442   0.07469   0.07277  -0.0443   0.9994   0.0265
  -9.750  -0.3485   0.06781   0.06589  -0.0492   0.9978   0.0270
  -9.500  -0.5539   0.05612   0.05344  -0.0609   0.9916   0.0253
  -9.250  -0.5432   0.05200   0.04927  -0.0626   0.9872   0.0256
  -9.000  -0.5255   0.04919   0.04640  -0.0644   0.9841   0.0260
  -8.750  -0.5545   0.03709   0.03347  -0.0619   0.9745   0.0195
  -8.500  -0.5432   0.03205   0.02796  -0.0618   0.9708   0.0191
  -8.250  -0.5349   0.02820   0.02366  -0.0596   0.9641   0.0187
  -8.000  -0.5152   0.02472   0.01970  -0.0588   0.9600   0.0184
  -7.750  -0.4860   0.02228   0.01692  -0.0594   0.9577   0.0186
  -7.500  -0.4519   0.02057   0.01495  -0.0607   0.9561   0.0192
  -7.250  -0.4255   0.01925   0.01342  -0.0602   0.9507   0.0196
  -7.000  -0.3930   0.01817   0.01218  -0.0609   0.9464   0.0200
  -6.750  -0.3581   0.01661   0.01050  -0.0623   0.9432   0.0207
  -6.500  -0.3216   0.01562   0.00953  -0.0641   0.9402   0.0219
  -6.250  -0.2971   0.01511   0.00900  -0.0632   0.9312   0.0230
  -6.000  -0.2625   0.01436   0.00818  -0.0643   0.9256   0.0241
  -5.750  -0.2360   0.01393   0.00766  -0.0637   0.9153   0.0250
  -5.500  -0.2095   0.01288   0.00660  -0.0634   0.9055   0.0266
  -5.250  -0.1834   0.01240   0.00609  -0.0628   0.8932   0.0282
  -5.000  -0.1589   0.01207   0.00570  -0.0619   0.8787   0.0302
  -4.750  -0.1370   0.01153   0.00511  -0.0604   0.8621   0.0329
  -4.500  -0.1134   0.01120   0.00471  -0.0593   0.8425   0.0359
  -4.250  -0.0920   0.01085   0.00427  -0.0576   0.8164   0.0403
  -4.000  -0.0702   0.01062   0.00392  -0.0561   0.7849   0.0476
  -3.750  -0.0505   0.01039   0.00365  -0.0541   0.7518   0.0676
  -3.500  -0.0321   0.01015   0.00343  -0.0521   0.7226   0.1056
  -3.000   0.0016   0.00947   0.00308  -0.0477   0.6799   0.2422
  -2.750   0.0118   0.00886   0.00298  -0.0443   0.6650   0.3999
  -2.500   0.0279   0.00863   0.00304  -0.0418   0.6518   0.4854
  -2.250   0.0531   0.00879   0.00312  -0.0410   0.6395   0.5285
  -2.000   0.0781   0.00894   0.00316  -0.0402   0.6291   0.5471
  -1.750   0.1024   0.00906   0.00317  -0.0393   0.6191   0.5622
  -1.500   0.1266   0.00910   0.00314  -0.0384   0.6102   0.5758
  -1.250   0.1510   0.00910   0.00306  -0.0376   0.6017   0.5860
  -1.000   0.1765   0.00904   0.00297  -0.0371   0.5938   0.5921
  -0.750   0.2014   0.00902   0.00288  -0.0364   0.5859   0.5993
  -0.500   0.2261   0.00890   0.00277  -0.0358   0.5789   0.6075
  -0.250   0.2499   0.00879   0.00265  -0.0350   0.5716   0.6181
   0.000   0.2716   0.00860   0.00253  -0.0337   0.5649   0.6312
   0.250   0.2876   0.00853   0.00279  -0.0311   0.5582   0.6577
   0.500   0.3107   0.00942   0.00390  -0.0289   0.5518   0.6878
   0.750   0.3394   0.00899   0.00320  -0.0300   0.5444   0.7486
   1.000   0.3653   0.00914   0.00325  -0.0296   0.5360   0.7531
   1.250   0.3910   0.00924   0.00332  -0.0292   0.5264   0.7569
   1.500   0.4164   0.00940   0.00339  -0.0288   0.5179   0.7605
   1.750   0.4426   0.00949   0.00345  -0.0285   0.5101   0.7634
   2.000   0.4681   0.00964   0.00351  -0.0281   0.5024   0.7655
   2.250   0.4940   0.00972   0.00361  -0.0278   0.4937   0.7672
   2.500   0.5189   0.00987   0.00370  -0.0272   0.4850   0.7690
   2.750   0.5442   0.00997   0.00381  -0.0268   0.4749   0.7714
   3.000   0.5689   0.01010   0.00391  -0.0263   0.4646   0.7738
   3.250   0.5928   0.01026   0.00400  -0.0256   0.4530   0.7761
   3.500   0.6172   0.01039   0.00411  -0.0251   0.4404   0.7780
   3.750   0.6410   0.01056   0.00421  -0.0245   0.4264   0.7794
   4.000   0.6638   0.01069   0.00430  -0.0237   0.4103   0.7808
   4.250   0.6859   0.01087   0.00444  -0.0228   0.3936   0.7826
   4.500   0.7077   0.01109   0.00459  -0.0218   0.3779   0.7846
   4.750   0.7296   0.01131   0.00476  -0.0209   0.3636   0.7864
   5.000   0.7514   0.01154   0.00494  -0.0200   0.3515   0.7882
   5.250   0.7730   0.01177   0.00513  -0.0191   0.3407   0.7893
   5.500   0.7945   0.01201   0.00531  -0.0182   0.3303   0.7902
   5.750   0.8166   0.01221   0.00550  -0.0175   0.3212   0.7910
   6.000   0.8363   0.01248   0.00571  -0.0162   0.3121   0.7918
   6.250   0.8580   0.01266   0.00590  -0.0154   0.3042   0.7925
   6.750   0.8977   0.01305   0.00628  -0.0131   0.2893   0.7939
   7.000   0.9160   0.01326   0.00648  -0.0117   0.2821   0.7946
   7.250   0.9363   0.01342   0.00668  -0.0107   0.2750   0.7955
   7.500   0.9546   0.01367   0.00691  -0.0093   0.2671   0.7962
   7.750   0.9743   0.01389   0.00716  -0.0082   0.2597   0.7971
   8.000   0.9916   0.01419   0.00745  -0.0067   0.2509   0.7980
   8.250   1.0105   0.01444   0.00772  -0.0056   0.2410   0.7990
   8.500   1.0270   0.01478   0.00804  -0.0041   0.2299   0.8000
   8.750   1.0423   0.01517   0.00839  -0.0024   0.2170   0.8008
   9.000   1.0566   0.01561   0.00878  -0.0006   0.2028   0.8015
   9.250   1.0700   0.01609   0.00921   0.0012   0.1895   0.8021
   9.500   1.0822   0.01663   0.00969   0.0032   0.1755   0.8027
   9.750   1.0953   0.01714   0.01018   0.0050   0.1650   0.8033
  10.000   1.1072   0.01769   0.01073   0.0069   0.1569   0.8041
  10.250   1.1183   0.01830   0.01131   0.0089   0.1499   0.8047
  10.500   1.1307   0.01887   0.01190   0.0106   0.1449   0.8051
  10.750   1.1426   0.01947   0.01251   0.0122   0.1396   0.8054
  11.000   1.1508   0.02026   0.01328   0.0143   0.1341   0.8058
  11.250   1.1647   0.02081   0.01389   0.0155   0.1299   0.8061
  11.500   1.1751   0.02154   0.01463   0.0171   0.1252   0.8064
  11.750   1.1809   0.02252   0.01560   0.0191   0.1200   0.8066
  12.000   1.1957   0.02305   0.01622   0.0200   0.1163   0.8070
  12.250   1.2041   0.02394   0.01711   0.0214   0.1105   0.8074
  12.500   1.2127   0.02487   0.01808   0.0227   0.1051   0.8077
  12.750   1.2210   0.02587   0.01907   0.0240   0.0961   0.8080
  13.000   1.2269   0.02708   0.02024   0.0252   0.0830   0.8083
  13.250   1.2108   0.02986   0.02278   0.0280   0.0537   0.8085
  13.500   1.2000   0.03253   0.02540   0.0299   0.0384   0.8086
  13.750   1.1790   0.03626   0.02906   0.0318   0.0213   0.8087
  14.000   1.1742   0.03889   0.03176   0.0326   0.0185   0.8088
  14.250   1.1745   0.04117   0.03413   0.0329   0.0179   0.8091
  14.500   1.1677   0.04424   0.03731   0.0332   0.0164   0.8091
  14.750   1.1664   0.04687   0.04005   0.0332   0.0159   0.8093
  15.000   1.1638   0.04973   0.04303   0.0331   0.0155   0.8095
  15.250   1.1609   0.05272   0.04613   0.0327   0.0151   0.8097
  15.500   1.1574   0.05584   0.04937   0.0323   0.0150   0.8100
  15.750   1.1490   0.05967   0.05332   0.0316   0.0145   0.8102
  16.000   1.1430   0.06334   0.05710   0.0307   0.0143   0.8104
  16.250   1.1310   0.06793   0.06181   0.0296   0.0139   0.8105
  16.500   1.1162   0.07308   0.06708   0.0282   0.0134   0.8105
  16.750   1.1097   0.07728   0.07139   0.0267   0.0135   0.8106
  17.000   1.0973   0.08247   0.07670   0.0250   0.0135   0.8107
  17.250   1.0829   0.08811   0.08246   0.0229   0.0133   0.8108
  17.500   1.0727   0.09322   0.08767   0.0209   0.0133   0.8110
  17.750   1.0517   0.10019   0.09476   0.0183   0.0129   0.8110
  18.000   1.0407   0.10565   0.10033   0.0161   0.0130   0.8111
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