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EPPLER 426 AIRFOIL (e426-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 426 AIRFOIL (e426-il)
Reynolds number: 100,000
Max Cl/Cd: 38.49 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e426-il-100000-n5.txt
Download as CSV file: xf-e426-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 426 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.8607   0.08581   0.08010  -0.0111   1.0000   0.0414
 -13.000  -0.8974   0.07469   0.06882  -0.0182   1.0000   0.0412
 -12.750  -0.9266   0.06535   0.05933  -0.0247   1.0000   0.0409
 -12.500  -0.9515   0.05733   0.05112  -0.0306   1.0000   0.0408
 -12.250  -0.9714   0.05093   0.04451  -0.0353   1.0000   0.0411
 -12.000  -0.9869   0.04609   0.03947  -0.0380   1.0000   0.0416
 -11.750  -0.9964   0.04296   0.03627  -0.0387   1.0000   0.0424
 -11.500  -1.0023   0.04061   0.03385  -0.0378   1.0000   0.0436
 -11.250  -1.0011   0.03845   0.03156  -0.0370   1.0000   0.0454
 -11.000  -0.9965   0.03624   0.02911  -0.0361   1.0000   0.0480
 -10.750  -0.9860   0.03482   0.02767  -0.0353   1.0000   0.0509
 -10.500  -0.9740   0.03313   0.02575  -0.0345   1.0000   0.0554
 -10.250  -0.9585   0.03207   0.02466  -0.0338   1.0000   0.0597
 -10.000  -0.9423   0.03081   0.02323  -0.0330   1.0000   0.0658
  -9.750  -0.9247   0.02965   0.02182  -0.0323   1.0000   0.0729
  -9.500  -0.9055   0.02895   0.02110  -0.0316   1.0000   0.0790
  -9.250  -0.8860   0.02801   0.01993  -0.0309   1.0000   0.0861
  -9.000  -0.8647   0.02754   0.01942  -0.0302   1.0000   0.0924
  -8.750  -0.8434   0.02686   0.01856  -0.0296   1.0000   0.0987
  -8.500  -0.8210   0.02647   0.01809  -0.0289   1.0000   0.1045
  -8.250  -0.7988   0.02580   0.01720  -0.0283   1.0000   0.1103
  -8.000  -0.7756   0.02547   0.01685  -0.0277   1.0000   0.1153
  -7.750  -0.7527   0.02479   0.01587  -0.0270   1.0000   0.1213
  -7.500  -0.7293   0.02439   0.01551  -0.0264   1.0000   0.1259
  -7.250  -0.7057   0.02395   0.01496  -0.0258   1.0000   0.1317
  -7.000  -0.6822   0.02328   0.01408  -0.0251   1.0000   0.1369
  -6.750  -0.6582   0.02265   0.01346  -0.0245   1.0000   0.1404
  -6.500  -0.6341   0.02196   0.01270  -0.0238   1.0000   0.1439
  -6.250  -0.6098   0.02128   0.01189  -0.0232   1.0000   0.1480
  -6.000  -0.5856   0.02062   0.01111  -0.0225   1.0000   0.1521
  -5.750  -0.5617   0.02003   0.01057  -0.0218   1.0000   0.1560
  -5.500  -0.5376   0.01947   0.00997  -0.0210   1.0000   0.1605
  -5.250  -0.5133   0.01893   0.00932  -0.0203   1.0000   0.1655
  -5.000  -0.4897   0.01836   0.00880  -0.0195   1.0000   0.1700
  -4.750  -0.4661   0.01789   0.00836  -0.0187   1.0000   0.1755
  -4.500  -0.4422   0.01749   0.00788  -0.0178   1.0000   0.1823
  -4.250  -0.4192   0.01702   0.00751  -0.0170   1.0000   0.1885
  -4.000  -0.3959   0.01665   0.00715  -0.0161   1.0000   0.1958
  -3.750  -0.3730   0.01625   0.00680  -0.0152   1.0000   0.2027
  -3.500  -0.3505   0.01591   0.00652  -0.0143   1.0000   0.2103
  -3.250  -0.3284   0.01560   0.00625  -0.0133   1.0000   0.2182
  -3.000  -0.3071   0.01531   0.00604  -0.0123   1.0000   0.2275
  -2.750  -0.2683   0.01499   0.00583  -0.0147   0.9873   0.2415
  -2.500  -0.2285   0.01465   0.00563  -0.0173   0.9720   0.2606
  -2.250  -0.1905   0.01428   0.00543  -0.0194   0.9542   0.2869
  -2.000  -0.1531   0.01386   0.00528  -0.0213   0.9349   0.3260
  -1.750  -0.1128   0.01343   0.00515  -0.0236   0.9137   0.3868
  -1.500  -0.0737   0.01309   0.00504  -0.0253   0.8849   0.4542
  -1.250  -0.0393   0.01288   0.00494  -0.0257   0.8482   0.5094
  -1.000  -0.0109   0.01276   0.00488  -0.0249   0.8107   0.5561
  -0.500   0.0414   0.01265   0.00482  -0.0227   0.7505   0.6350
  -0.250   0.0672   0.01264   0.00480  -0.0215   0.7239   0.6688
   0.000   0.0927   0.01263   0.00480  -0.0203   0.6971   0.7023
   0.250   0.1179   0.01263   0.00481  -0.0191   0.6707   0.7352
   0.500   0.1429   0.01264   0.00481  -0.0177   0.6437   0.7680
   0.750   0.1679   0.01264   0.00482  -0.0163   0.6158   0.8031
   1.000   0.1941   0.01265   0.00484  -0.0151   0.5877   0.8457
   1.250   0.2276   0.01269   0.00486  -0.0152   0.5558   0.9001
   1.500   0.2718   0.01280   0.00486  -0.0178   0.5154   0.9540
   1.750   0.3167   0.01298   0.00482  -0.0211   0.4703   0.9929
   2.000   0.3428   0.01322   0.00484  -0.0209   0.4320   1.0000
   2.250   0.3648   0.01351   0.00491  -0.0198   0.3969   1.0000
   2.500   0.3876   0.01383   0.00502  -0.0189   0.3641   1.0000
   2.750   0.4109   0.01419   0.00517  -0.0180   0.3365   1.0000
   3.000   0.4347   0.01456   0.00537  -0.0173   0.3148   1.0000
   3.250   0.4589   0.01494   0.00560  -0.0166   0.2978   1.0000
   3.500   0.4834   0.01532   0.00586  -0.0159   0.2833   1.0000
   3.750   0.5081   0.01572   0.00615  -0.0153   0.2711   1.0000
   4.000   0.5328   0.01614   0.00646  -0.0147   0.2606   1.0000
   4.250   0.5581   0.01651   0.00681  -0.0142   0.2507   1.0000
   4.500   0.5828   0.01698   0.00717  -0.0136   0.2426   1.0000
   4.750   0.6085   0.01736   0.00758  -0.0131   0.2342   1.0000
   5.000   0.6333   0.01785   0.00798  -0.0126   0.2273   1.0000
   5.250   0.6590   0.01826   0.00845  -0.0121   0.2196   1.0000
   5.500   0.6841   0.01873   0.00889  -0.0116   0.2126   1.0000
   5.750   0.7094   0.01922   0.00940  -0.0111   0.2060   1.0000
   6.000   0.7346   0.01969   0.00992  -0.0106   0.1991   1.0000
   6.250   0.7593   0.02025   0.01041  -0.0101   0.1931   1.0000
   6.500   0.7845   0.02073   0.01104  -0.0096   0.1859   1.0000
   6.750   0.8091   0.02126   0.01157  -0.0090   0.1799   1.0000
   7.000   0.8337   0.02185   0.01223  -0.0085   0.1737   1.0000
   7.250   0.8581   0.02239   0.01286  -0.0079   0.1670   1.0000
   7.500   0.8820   0.02300   0.01341  -0.0074   0.1618   1.0000
   7.750   0.9060   0.02361   0.01424  -0.0068   0.1550   1.0000
   8.000   0.9295   0.02415   0.01482  -0.0062   0.1492   1.0000
   8.250   0.9527   0.02483   0.01561  -0.0056   0.1436   1.0000
   8.500   0.9756   0.02544   0.01635  -0.0049   0.1373   1.0000
   8.750   0.9979   0.02604   0.01692  -0.0042   0.1326   1.0000
   9.000   1.0199   0.02681   0.01794  -0.0035   0.1263   1.0000
   9.250   1.0414   0.02743   0.01862  -0.0028   0.1215   1.0000
   9.500   1.0622   0.02828   0.01960  -0.0020   0.1167   1.0000
   9.750   1.0825   0.02913   0.02060  -0.0012   0.1117   1.0000
  10.000   1.1022   0.02988   0.02136  -0.0003   0.1078   1.0000
  10.250   1.1205   0.03102   0.02272   0.0006   0.1034   1.0000
  10.500   1.1382   0.03207   0.02392   0.0016   0.0993   1.0000
  10.750   1.1553   0.03304   0.02492   0.0026   0.0961   1.0000
  11.000   1.1703   0.03444   0.02650   0.0036   0.0928   1.0000
  11.250   1.1833   0.03587   0.02818   0.0048   0.0891   1.0000
  11.500   1.1961   0.03699   0.02939   0.0060   0.0858   1.0000
  11.750   1.2074   0.03820   0.03060   0.0073   0.0829   1.0000
  12.000   1.2113   0.04002   0.03276   0.0089   0.0794   1.0000
  12.250   1.2133   0.04151   0.03441   0.0107   0.0765   1.0000
  12.500   1.2157   0.04283   0.03576   0.0122   0.0739   1.0000
  12.750   1.2123   0.04497   0.03805   0.0132   0.0715   1.0000
  13.000   1.2038   0.04799   0.04134   0.0133   0.0692   1.0000
  13.250   1.1955   0.05124   0.04477   0.0126   0.0670   1.0000
  13.500   1.1878   0.05481   0.04847   0.0112   0.0654   1.0000
  13.750   1.1817   0.05835   0.05203   0.0093   0.0635   1.0000
  14.000   1.1635   0.06427   0.05816   0.0059   0.0626   1.0000
  14.250   1.1374   0.07205   0.06618   0.0010   0.0620   1.0000
  14.500   1.1053   0.08150   0.07585  -0.0050   0.0621   1.0000
  14.750   1.0619   0.09388   0.08840  -0.0128   0.0627   1.0000
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