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EPPLER 340 AIRFOIL (e340-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 340 AIRFOIL (e340-il)
Reynolds number: 1,000,000
Max Cl/Cd: 93.7 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e340-il-1000000-n5.txt
Download as CSV file: xf-e340-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 340 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6271   0.08265   0.08019  -0.0003   0.6564   0.0040
 -10.000  -0.6564   0.07397   0.07142  -0.0057   0.6518   0.0040
  -9.750  -0.6826   0.06796   0.06529  -0.0061   0.6440   0.0040
  -9.500  -0.7084   0.06242   0.05960  -0.0040   0.6368   0.0040
  -9.250  -0.7345   0.05622   0.05319  -0.0003   0.6298   0.0041
  -9.000  -0.8424   0.02985   0.02541   0.0150   0.6486   0.0041
  -8.750  -0.8338   0.02679   0.02193   0.0177   0.6353   0.0041
  -8.500  -0.8197   0.02452   0.01930   0.0199   0.6213   0.0041
  -8.250  -0.8013   0.02296   0.01746   0.0213   0.6067   0.0041
  -8.000  -0.7816   0.02146   0.01571   0.0227   0.5931   0.0041
  -7.750  -0.7597   0.02036   0.01439   0.0237   0.5799   0.0042
  -7.500  -0.7366   0.01949   0.01334   0.0245   0.5685   0.0042
  -7.250  -0.7129   0.01864   0.01233   0.0252   0.5574   0.0043
  -7.000  -0.6885   0.01792   0.01147   0.0258   0.5472   0.0043
  -6.750  -0.6636   0.01733   0.01075   0.0264   0.5367   0.0044
  -6.500  -0.6385   0.01673   0.01002   0.0269   0.5251   0.0044
  -6.250  -0.6133   0.01610   0.00927   0.0274   0.5152   0.0044
  -6.000  -0.5886   0.01533   0.00836   0.0280   0.5056   0.0044
  -5.750  -0.5637   0.01467   0.00761   0.0286   0.4972   0.0045
  -5.500  -0.5391   0.01404   0.00687   0.0293   0.4887   0.0045
  -5.250  -0.5141   0.01354   0.00630   0.0299   0.4809   0.0045
  -4.750  -0.4639   0.01269   0.00530   0.0310   0.4649   0.0046
  -4.250  -0.4130   0.01202   0.00452   0.0321   0.4493   0.0048
  -4.000  -0.3872   0.01175   0.00421   0.0325   0.4420   0.0050
  -3.750  -0.3612   0.01152   0.00393   0.0329   0.4360   0.0051
  -3.500  -0.3352   0.01130   0.00368   0.0333   0.4296   0.0053
  -3.000  -0.2828   0.01093   0.00322   0.0341   0.4170   0.0061
  -2.750  -0.2566   0.01077   0.00302   0.0345   0.4104   0.0066
  -2.500  -0.2305   0.01061   0.00285   0.0349   0.4050   0.0079
  -2.250  -0.2041   0.01046   0.00269   0.0352   0.4001   0.0101
  -2.000  -0.1777   0.01033   0.00255   0.0355   0.3948   0.0144
  -1.750  -0.1517   0.01018   0.00242   0.0359   0.3898   0.0244
  -1.500  -0.1257   0.01002   0.00231   0.0363   0.3853   0.0401
  -1.250  -0.1004   0.00982   0.00221   0.0368   0.3799   0.0713
  -1.000  -0.0763   0.00955   0.00211   0.0374   0.3750   0.1271
  -0.750  -0.0645   0.00846   0.00188   0.0402   0.3720   0.3761
  -0.500  -0.0866   0.00639   0.00149   0.0503   0.3703   0.7915
  -0.250  -0.0630   0.00654   0.00186   0.0517   0.3661   0.8709
   0.000  -0.0372   0.00668   0.00192   0.0523   0.3614   0.8832
   0.250  -0.0083   0.00693   0.00215   0.0524   0.3572   0.8912
   0.500   0.0178   0.00708   0.00225   0.0530   0.3540   0.8984
   0.750   0.0479   0.00732   0.00248   0.0528   0.3505   0.9030
   1.000   0.0766   0.00751   0.00263   0.0528   0.3469   0.9065
   1.250   0.1042   0.00759   0.00266   0.0529   0.3433   0.9084
   1.500   0.1319   0.00761   0.00264   0.0529   0.3403   0.9095
   1.750   0.1597   0.00763   0.00262   0.0528   0.3370   0.9106
   2.000   0.1874   0.00765   0.00260   0.0528   0.3332   0.9114
   2.250   0.2151   0.00770   0.00260   0.0527   0.3293   0.9123
   2.500   0.2429   0.00774   0.00260   0.0526   0.3260   0.9130
   2.750   0.2712   0.00776   0.00260   0.0525   0.3238   0.9135
   3.000   0.2995   0.00778   0.00261   0.0523   0.3212   0.9141
   3.250   0.3277   0.00782   0.00263   0.0521   0.3183   0.9145
   3.500   0.3559   0.00788   0.00266   0.0519   0.3148   0.9151
   3.750   0.3838   0.00795   0.00272   0.0518   0.3111   0.9157
   4.000   0.4121   0.00800   0.00276   0.0516   0.3086   0.9162
   4.250   0.4403   0.00805   0.00281   0.0514   0.3056   0.9167
   4.500   0.4684   0.00811   0.00286   0.0512   0.3026   0.9171
   4.750   0.4964   0.00819   0.00293   0.0510   0.2996   0.9176
   5.000   0.5242   0.00828   0.00300   0.0508   0.2960   0.9181
   5.250   0.5523   0.00834   0.00307   0.0506   0.2934   0.9186
   5.500   0.5804   0.00841   0.00314   0.0504   0.2904   0.9191
   5.750   0.6083   0.00848   0.00322   0.0501   0.2866   0.9197
   6.000   0.6359   0.00859   0.00332   0.0500   0.2823   0.9202
   6.250   0.6637   0.00869   0.00341   0.0497   0.2789   0.9208
   6.500   0.6916   0.00877   0.00352   0.0495   0.2754   0.9214
   6.750   0.7193   0.00887   0.00362   0.0493   0.2709   0.9221
   7.000   0.7466   0.00901   0.00375   0.0491   0.2657   0.9228
   7.250   0.7744   0.00910   0.00386   0.0488   0.2611   0.9233
   7.500   0.8020   0.00922   0.00399   0.0486   0.2563   0.9239
   7.750   0.8291   0.00938   0.00414   0.0484   0.2508   0.9244
   8.000   0.8567   0.00951   0.00428   0.0481   0.2456   0.9250
   8.250   0.8836   0.00969   0.00445   0.0479   0.2377   0.9255
   8.500   0.9108   0.00986   0.00463   0.0476   0.2312   0.9261
   8.750   0.9374   0.01008   0.00483   0.0474   0.2235   0.9266
   9.000   0.9642   0.01029   0.00504   0.0472   0.2151   0.9271
   9.250   0.9901   0.01057   0.00530   0.0470   0.2049   0.9276
   9.500   1.0158   0.01086   0.00557   0.0468   0.1949   0.9281
   9.750   1.0408   0.01115   0.00585   0.0469   0.1848   0.9287
  10.000   1.0646   0.01153   0.00620   0.0470   0.1723   0.9294
  10.250   1.0883   0.01190   0.00656   0.0472   0.1621   0.9301
  10.500   1.1109   0.01236   0.00698   0.0474   0.1493   0.9308
  10.750   1.1322   0.01290   0.00748   0.0478   0.1346   0.9317
  11.000   1.1527   0.01349   0.00802   0.0482   0.1203   0.9328
  11.250   1.1727   0.01410   0.00859   0.0487   0.1074   0.9338
  11.500   1.1918   0.01477   0.00921   0.0492   0.0952   0.9347
  11.750   1.2099   0.01548   0.00989   0.0497   0.0836   0.9358
  12.000   1.2264   0.01627   0.01065   0.0504   0.0726   0.9370
  12.250   1.2399   0.01710   0.01145   0.0514   0.0631   0.9384
  12.500   1.2531   0.01801   0.01236   0.0522   0.0558   0.9398
  12.750   1.2640   0.01922   0.01356   0.0527   0.0478   0.9413
  13.000   1.2721   0.02055   0.01492   0.0532   0.0424   0.9430
  13.250   1.2791   0.02214   0.01657   0.0533   0.0381   0.9449
  13.500   1.2835   0.02428   0.01875   0.0527   0.0337   0.9470
  13.750   1.2867   0.02681   0.02133   0.0517   0.0296   0.9492
  14.000   1.2897   0.02951   0.02409   0.0504   0.0265   0.9512
  14.250   1.2890   0.03272   0.02736   0.0488   0.0237   0.9532
  14.500   1.2845   0.03575   0.03047   0.0484   0.0217   0.9556
  14.750   1.2760   0.03924   0.03404   0.0479   0.0200   0.9581
  15.000   1.2695   0.04264   0.03753   0.0472   0.0188   0.9605
  15.250   1.2616   0.04636   0.04133   0.0462   0.0175   0.9627
  15.500   1.2490   0.04993   0.04498   0.0463   0.0168   0.9655
  15.750   1.2273   0.05314   0.04828   0.0488   0.0163   0.9707
  16.000   1.2097   0.05639   0.05161   0.0506   0.0158   0.9767
  16.500   1.1930   0.06421   0.05958   0.0485   0.0139   0.9883
  16.750   1.1847   0.06834   0.06376   0.0470   0.0131   0.9919
  17.000   1.1783   0.07212   0.06762   0.0460   0.0125   0.9947
  17.500   1.1660   0.08043   0.07606   0.0423   0.0108   0.9969
  17.750   1.1602   0.08464   0.08034   0.0403   0.0102   0.9978
  18.000   1.1547   0.08853   0.08430   0.0387   0.0096   0.9995
  18.250   1.1485   0.09272   0.08855   0.0369   0.0091   1.0000
  18.500   1.1425   0.09688   0.09278   0.0352   0.0087   1.0000
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