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EPPLER 343 AIRFOIL (e343-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 343 AIRFOIL (e343-il)
Reynolds number: 500,000
Max Cl/Cd: 87.93 at α=10.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e343-il-500000-n5.txt
Download as CSV file: xf-e343-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 343 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1961   0.07406   0.07059  -0.0515   0.6124   0.0114
  -8.500  -0.2936   0.06337   0.05967  -0.0654   0.6111   0.0086
  -8.250  -0.3038   0.06094   0.05718  -0.0636   0.6020   0.0085
  -8.000  -0.3136   0.05845   0.05459  -0.0612   0.5936   0.0084
  -7.750  -0.3165   0.05572   0.05176  -0.0595   0.5848   0.0083
  -7.250  -0.3463   0.04275   0.03823  -0.0517   0.5751   0.0064
  -7.000  -0.3414   0.03997   0.03525  -0.0492   0.5669   0.0064
  -6.750  -0.3388   0.03612   0.03112  -0.0459   0.5595   0.0063
  -6.500  -0.3335   0.03228   0.02696  -0.0426   0.5525   0.0062
  -6.250  -0.3345   0.02579   0.01984  -0.0375   0.5476   0.0060
  -6.000  -0.3236   0.02157   0.01496  -0.0341   0.5406   0.0060
  -5.750  -0.3034   0.01943   0.01241  -0.0325   0.5333   0.0060
  -5.500  -0.2803   0.01791   0.01054  -0.0313   0.5252   0.0062
  -5.250  -0.2561   0.01698   0.00938  -0.0305   0.5177   0.0064
  -5.000  -0.2316   0.01609   0.00832  -0.0297   0.5097   0.0066
  -4.750  -0.2075   0.01546   0.00756  -0.0290   0.5018   0.0067
  -4.500  -0.1828   0.01503   0.00707  -0.0283   0.4940   0.0071
  -4.250  -0.1583   0.01462   0.00657  -0.0276   0.4867   0.0073
  -4.000  -0.1337   0.01421   0.00609  -0.0269   0.4805   0.0076
  -3.750  -0.1093   0.01382   0.00562  -0.0261   0.4739   0.0081
  -3.250  -0.0606   0.01320   0.00486  -0.0246   0.4625   0.0086
  -3.000  -0.0366   0.01288   0.00449  -0.0237   0.4563   0.0091
  -2.750  -0.0124   0.01267   0.00422  -0.0230   0.4505   0.0097
  -2.500   0.0128   0.01250   0.00403  -0.0224   0.4451   0.0109
  -2.250   0.0373   0.01229   0.00378  -0.0217   0.4397   0.0120
  -2.000   0.0618   0.01213   0.00357  -0.0209   0.4349   0.0133
  -1.750   0.0867   0.01194   0.00336  -0.0202   0.4307   0.0150
  -1.500   0.1117   0.01178   0.00319  -0.0196   0.4262   0.0183
  -1.250   0.1364   0.01164   0.00304  -0.0189   0.4216   0.0256
  -0.750   0.1848   0.01129   0.00286  -0.0175   0.4133   0.0786
  -0.500   0.2078   0.01102   0.00278  -0.0166   0.4091   0.1436
  -0.250   0.1997   0.00900   0.00249  -0.0102   0.4065   0.6394
   0.000   0.2087   0.00885   0.00311  -0.0051   0.4034   0.8689
   0.250   0.2303   0.00912   0.00330  -0.0034   0.3999   0.8900
   0.500   0.2532   0.00926   0.00340  -0.0020   0.3970   0.9030
   0.750   0.2777   0.00939   0.00350  -0.0009   0.3937   0.9130
   1.000   0.3051   0.00961   0.00369  -0.0002   0.3900   0.9214
   1.250   0.3345   0.00986   0.00388  -0.0002   0.3862   0.9263
   1.500   0.3616   0.00995   0.00389   0.0000   0.3830   0.9277
   1.750   0.3883   0.00998   0.00388   0.0001   0.3804   0.9288
   2.000   0.4142   0.01000   0.00386   0.0005   0.3776   0.9300
   2.250   0.4389   0.01002   0.00384   0.0010   0.3744   0.9317
   2.500   0.4650   0.01007   0.00384   0.0013   0.3712   0.9326
   2.750   0.4918   0.01016   0.00388   0.0014   0.3682   0.9332
   3.000   0.5188   0.01023   0.00392   0.0015   0.3658   0.9338
   3.250   0.5460   0.01030   0.00398   0.0015   0.3632   0.9346
   3.500   0.5728   0.01037   0.00404   0.0016   0.3604   0.9354
   3.750   0.5991   0.01044   0.00409   0.0018   0.3573   0.9362
   4.000   0.6249   0.01053   0.00415   0.0020   0.3547   0.9370
   4.250   0.6503   0.01062   0.00422   0.0023   0.3520   0.9380
   4.500   0.6757   0.01071   0.00429   0.0026   0.3495   0.9390
   4.750   0.7015   0.01076   0.00436   0.0029   0.3471   0.9400
   5.000   0.7277   0.01085   0.00446   0.0030   0.3444   0.9408
   5.250   0.7540   0.01096   0.00457   0.0031   0.3417   0.9416
   5.500   0.7797   0.01108   0.00468   0.0033   0.3388   0.9425
   5.750   0.8049   0.01121   0.00480   0.0036   0.3360   0.9433
   6.000   0.8302   0.01134   0.00494   0.0039   0.3337   0.9442
   6.250   0.8560   0.01142   0.00506   0.0041   0.3312   0.9452
   6.500   0.8811   0.01152   0.00519   0.0043   0.3283   0.9463
   6.750   0.9056   0.01164   0.00533   0.0047   0.3252   0.9476
   7.000   0.9300   0.01177   0.00547   0.0051   0.3222   0.9486
   7.250   0.9540   0.01194   0.00563   0.0055   0.3191   0.9498
   7.500   0.9790   0.01205   0.00579   0.0058   0.3162   0.9510
   7.750   1.0033   0.01217   0.00596   0.0062   0.3129   0.9525
   8.000   1.0264   0.01230   0.00612   0.0068   0.3093   0.9544
   8.250   1.0490   0.01247   0.00630   0.0074   0.3060   0.9563
   8.500   1.0714   0.01264   0.00650   0.0081   0.3025   0.9584
   8.750   1.0944   0.01276   0.00669   0.0087   0.2989   0.9607
   9.000   1.1164   0.01291   0.00688   0.0094   0.2948   0.9628
   9.250   1.1384   0.01311   0.00710   0.0100   0.2904   0.9646
   9.500   1.1599   0.01329   0.00732   0.0108   0.2865   0.9669
   9.750   1.1804   0.01345   0.00754   0.0118   0.2812   0.9695
  10.000   1.2019   0.01367   0.00780   0.0124   0.2761   0.9714
  10.250   1.2231   0.01391   0.00808   0.0131   0.2708   0.9738
  10.500   1.2436   0.01416   0.00838   0.0139   0.2643   0.9768
  10.750   1.2665   0.01453   0.00877   0.0139   0.2580   0.9787
  11.000   1.2907   0.01488   0.00917   0.0138   0.2500   0.9805
  11.250   1.3127   0.01533   0.00964   0.0138   0.2423   0.9829
  11.500   1.3339   0.01582   0.01016   0.0139   0.2330   0.9856
  11.750   1.3564   0.01641   0.01077   0.0135   0.2230   0.9878
  12.000   1.3765   0.01711   0.01150   0.0133   0.2135   0.9911
  12.250   1.3937   0.01796   0.01235   0.0134   0.2028   0.9964
  12.500   1.4031   0.01882   0.01324   0.0148   0.1929   1.0000
  12.750   1.4009   0.01986   0.01428   0.0181   0.1846   1.0000
  13.000   1.3998   0.02117   0.01559   0.0205   0.1755   1.0000
  13.250   1.4010   0.02260   0.01705   0.0223   0.1672   1.0000
  13.500   1.3987   0.02447   0.01894   0.0238   0.1591   1.0000
  13.750   1.3969   0.02651   0.02101   0.0249   0.1509   1.0000
  14.000   1.3920   0.02896   0.02349   0.0257   0.1427   1.0000
  14.250   1.3836   0.03188   0.02643   0.0264   0.1350   1.0000
  14.500   1.3793   0.03454   0.02916   0.0267   0.1288   1.0000
  14.750   1.3686   0.03792   0.03256   0.0270   0.1225   1.0000
  15.000   1.3619   0.04099   0.03570   0.0271   0.1174   1.0000
  15.250   1.3498   0.04466   0.03941   0.0270   0.1116   1.0000
  15.500   1.3399   0.04823   0.04304   0.0268   0.1073   1.0000
  15.750   1.3289   0.05203   0.04689   0.0264   0.1019   1.0000
  16.000   1.3162   0.05615   0.05105   0.0258   0.0978   1.0000
  16.250   1.3095   0.05968   0.05465   0.0253   0.0935   1.0000
  16.500   1.2969   0.06398   0.05899   0.0244   0.0885   1.0000
  16.750   1.2878   0.06798   0.06304   0.0235   0.0844   1.0000
  17.000   1.2784   0.07207   0.06717   0.0225   0.0794   1.0000
  17.250   1.2684   0.07633   0.07147   0.0214   0.0759   1.0000
  17.500   1.2632   0.08005   0.07525   0.0203   0.0720   1.0000
  17.750   1.2560   0.08407   0.07933   0.0191   0.0685   1.0000
  18.000   1.2487   0.08817   0.08346   0.0178   0.0651   1.0000
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