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E471 (6.25%) (e471-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E471 (6.25%) (e471-il)
Reynolds number: 200,000
Max Cl/Cd: 105.46 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e471-il-200000.txt
Download as CSV file: xf-e471-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E471  (6.25%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3837   0.10615   0.10293  -0.0242   1.0000   0.0280
  -7.500  -0.3937   0.10503   0.10187  -0.0222   1.0000   0.0281
  -7.250  -0.4058   0.10401   0.10092  -0.0201   1.0000   0.0281
  -7.000  -0.4097   0.10209   0.09904  -0.0198   1.0000   0.0282
  -6.750  -0.4114   0.09988   0.09688  -0.0203   1.0000   0.0283
  -6.500  -0.4109   0.09729   0.09432  -0.0215   1.0000   0.0283
  -6.250  -0.4096   0.09102   0.08809  -0.0209   0.9986   0.0293
  -6.000  -0.3944   0.08738   0.08444  -0.0205   0.9961   0.0307
  -5.750  -0.3718   0.08344   0.08049  -0.0255   0.9920   0.0323
  -5.500  -0.3458   0.07909   0.07611  -0.0325   0.9870   0.0346
  -5.250  -0.3027   0.07361   0.07057  -0.0462   0.9830   0.0384
  -5.000  -0.2402   0.06713   0.06389  -0.0672   0.9760   0.0401
  -4.750  -0.2292   0.06106   0.05788  -0.0684   0.9730   0.0419
  -4.500  -0.2034   0.05818   0.05495  -0.0708   0.9706   0.0449
  -4.250  -0.1338   0.04974   0.04606  -0.0906   0.9663   0.0542
  -4.000  -0.1169   0.04727   0.04370  -0.0902   0.9624   0.0567
  -3.750  -0.0739   0.04350   0.03974  -0.0969   0.9601   0.0631
  -3.500  -0.0214   0.03821   0.03412  -0.1063   0.9588   0.0706
  -2.500   0.1759   0.02198   0.01554  -0.1275   0.9558   0.0468
  -2.250   0.2117   0.02042   0.01340  -0.1285   0.9522   0.0411
  -2.000   0.2477   0.01951   0.01229  -0.1300   0.9492   0.0400
  -1.750   0.2863   0.01830   0.01096  -0.1321   0.9472   0.0400
  -1.500   0.3266   0.01717   0.00978  -0.1347   0.9456   0.0419
  -1.250   0.3617   0.01665   0.00924  -0.1363   0.9420   0.0484
  -1.000   0.3949   0.01620   0.00882  -0.1375   0.9370   0.0699
  -0.750   0.4359   0.01492   0.00878  -0.1410   0.9350   0.4409
  -0.500   0.4676   0.01401   0.00885  -0.1413   0.9326   0.7802
  -0.250   0.4898   0.01374   0.00869  -0.1398   0.9253   1.0000
   0.000   0.5273   0.01371   0.00852  -0.1417   0.9212   1.0000
   0.250   0.5690   0.01359   0.00828  -0.1443   0.9186   1.0000
   0.500   0.5969   0.01363   0.00824  -0.1443   0.9108   1.0000
   0.750   0.6374   0.01343   0.00798  -0.1467   0.9072   1.0000
   1.000   0.6818   0.01311   0.00762  -0.1497   0.9050   1.0000
   1.250   0.7103   0.01306   0.00756  -0.1496   0.8965   1.0000
   1.500   0.7544   0.01264   0.00714  -0.1524   0.8932   1.0000
   1.750   0.7887   0.01241   0.00692  -0.1534   0.8865   1.0000
   2.000   0.8271   0.01203   0.00656  -0.1549   0.8804   1.0000
   2.250   0.8614   0.01173   0.00633  -0.1557   0.8724   1.0000
   2.500   0.8996   0.01132   0.00596  -0.1571   0.8650   1.0000
   2.750   0.9295   0.01114   0.00583  -0.1570   0.8538   1.0000
   3.000   0.9603   0.01094   0.00568  -0.1570   0.8416   1.0000
   3.250   0.9905   0.01075   0.00558  -0.1568   0.8276   1.0000
   3.500   1.0202   0.01060   0.00547  -0.1565   0.8114   1.0000
   3.750   1.0472   0.01054   0.00546  -0.1558   0.7918   1.0000
   4.000   1.0744   0.01050   0.00544  -0.1550   0.7687   1.0000
   4.250   1.0994   0.01053   0.00554  -0.1539   0.7398   1.0000
   4.500   1.1231   0.01065   0.00561  -0.1524   0.6998   1.0000
   4.750   1.1443   0.01094   0.00573  -0.1504   0.6395   1.0000
   5.000   1.1584   0.01176   0.00598  -0.1472   0.5335   1.0000
   5.250   1.1653   0.01319   0.00662  -0.1431   0.4033   1.0000
   5.500   1.1766   0.01451   0.00739  -0.1403   0.3036   1.0000
   5.750   1.1898   0.01585   0.00827  -0.1380   0.2152   1.0000
   6.000   1.2023   0.01745   0.00925  -0.1358   0.1204   1.0000
   6.250   1.2096   0.02002   0.01110  -0.1324   0.0302   1.0000
   6.500   1.2240   0.02172   0.01289  -0.1298   0.0233   1.0000
   6.750   1.2410   0.02301   0.01434  -0.1277   0.0214   1.0000
   7.000   1.2571   0.02454   0.01600  -0.1255   0.0201   1.0000
   7.250   1.2742   0.02628   0.01786  -0.1235   0.0192   1.0000
   7.500   1.2941   0.02833   0.02004  -0.1220   0.0188   1.0000
   7.750   1.3182   0.03084   0.02277  -0.1210   0.0186   1.0000
   8.000   1.3436   0.03368   0.02589  -0.1202   0.0185   1.0000
   8.250   1.3629   0.03578   0.02817  -0.1190   0.0172   1.0000
   8.500   1.3810   0.03922   0.03185  -0.1178   0.0160   1.0000
   8.750   1.3975   0.04247   0.03553  -0.1158   0.0163   1.0000
   9.000   1.4070   0.04777   0.04164  -0.1120   0.0180   1.0000
   9.250   1.4035   0.05451   0.04910  -0.1074   0.0204   1.0000
   9.500   1.3957   0.06021   0.05521  -0.1035   0.0219   1.0000
   9.750   1.3063   0.05918   0.05479  -0.0889   0.0219   1.0000
  10.000   1.2832   0.06405   0.05991  -0.0845   0.0223   1.0000
  10.250   1.2567   0.07000   0.06607  -0.0811   0.0229   1.0000
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