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EPPLER 561 AIRFOIL (e561-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 561 AIRFOIL (e561-il)
Reynolds number: 50,000
Max Cl/Cd: 5.56 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e561-il-50000.txt
Download as CSV file: xf-e561-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 561 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.2269   0.14166   0.13459  -0.0377   1.0000   0.2146
 -11.250  -0.2361   0.14077   0.13379  -0.0379   1.0000   0.2202
 -11.000  -0.2575   0.14137   0.13454  -0.0382   1.0000   0.2217
 -10.750  -0.2240   0.13414   0.12729  -0.0365   1.0000   0.2286
 -10.500  -0.2299   0.13276   0.12602  -0.0359   1.0000   0.2357
 -10.250  -0.2549   0.13345   0.12686  -0.0355   1.0000   0.2381
 -10.000  -0.2326   0.12756   0.12100  -0.0341   1.0000   0.2423
  -9.750  -0.2323   0.12551   0.11902  -0.0325   1.0000   0.2502
  -9.500  -0.2551   0.12568   0.11937  -0.0310   1.0000   0.2540
  -9.250  -0.2819   0.12602   0.11988  -0.0290   1.0000   0.2550
  -9.000  -0.2535   0.12059   0.11445  -0.0264   1.0000   0.2666
  -8.750  -0.2779   0.12087   0.11488  -0.0239   1.0000   0.2703
  -8.500  -0.3061   0.12133   0.11552  -0.0212   1.0000   0.2715
  -8.250  -0.2897   0.11745   0.11166  -0.0184   1.0000   0.2825
  -8.000  -0.3142   0.11767   0.11202  -0.0158   1.0000   0.2868
  -7.750  -0.3422   0.11790   0.11240  -0.0134   1.0000   0.2883
  -7.500  -0.3308   0.11479   0.10931  -0.0109   1.0000   0.3004
  -7.250  -0.3574   0.11485   0.10951  -0.0086   1.0000   0.3045
  -7.000  -0.3850   0.11464   0.10942  -0.0065   1.0000   0.3057
  -6.750  -0.3408   0.10923   0.10388  -0.0095   0.9933   0.3330
  -6.500  -0.3210   0.10582   0.10041  -0.0138   0.9835   0.3549
  -6.250  -0.3065   0.10280   0.09732  -0.0172   0.9728   0.3749
  -6.000  -0.2904   0.09969   0.09414  -0.0199   0.9620   0.3933
  -5.750  -0.2741   0.09661   0.09099  -0.0221   0.9511   0.4110
  -5.500  -0.2597   0.09385   0.08817  -0.0238   0.9399   0.4290
  -5.250  -0.2457   0.09123   0.08548  -0.0254   0.9296   0.4474
  -5.000  -0.2350   0.08897   0.08316  -0.0264   0.9189   0.4666
  -4.750  -0.2258   0.08677   0.08092  -0.0260   0.9072   0.4834
  -4.500  -0.2955   0.06310   0.05675  -0.0679   0.8961   0.3260
  -4.250  -0.2593   0.06117   0.05459  -0.0721   0.8865   0.3436
  -4.000  -0.2459   0.06139   0.05481  -0.0691   0.8753   0.3536
  -3.750  -0.2089   0.05963   0.05284  -0.0731   0.8665   0.3697
  -3.500  -0.1838   0.05768   0.05067  -0.0766   0.8558   0.3831
  -3.250  -0.1476   0.05580   0.04850  -0.0817   0.8468   0.3988
  -3.000  -0.1208   0.05522   0.04780  -0.0827   0.8373   0.4117
  -2.750  -0.0978   0.05469   0.04717  -0.0833   0.8281   0.4229
  -2.500  -0.0610   0.05361   0.04586  -0.0871   0.8191   0.4379
  -2.250  -0.0302   0.05281   0.04479  -0.0909   0.8101   0.4522
  -2.000  -0.0066   0.05282   0.04479  -0.0900   0.8017   0.4630
  -1.750   0.0184   0.05257   0.04439  -0.0917   0.7931   0.4752
  -1.500   0.0521   0.05220   0.04381  -0.0949   0.7848   0.4896
  -1.250   0.0754   0.05240   0.04396  -0.0949   0.7774   0.5011
  -1.000   0.0940   0.05265   0.04412  -0.0954   0.7689   0.5119
  -0.750   0.1397   0.05230   0.04360  -0.0986   0.7624   0.5287
  -0.500   0.1378   0.05345   0.04474  -0.0968   0.7543   0.5364
  -0.250   0.1728   0.05351   0.04470  -0.0986   0.7475   0.5510
   0.000   0.1880   0.05436   0.04545  -0.0991   0.7404   0.5631
   0.250   0.2031   0.05520   0.04625  -0.0988   0.7336   0.5750
   0.500   0.2490   0.05516   0.04611  -0.1014   0.7277   0.5935
   0.750   0.2403   0.05697   0.04794  -0.0994   0.7218   0.6009
   1.000   0.2585   0.05801   0.04891  -0.1000   0.7157   0.6152
   1.250   0.3035   0.05812   0.04897  -0.1019   0.7096   0.6351
   1.500   0.2926   0.06024   0.05114  -0.0998   0.7060   0.6434
   1.750   0.2985   0.06187   0.05275  -0.0993   0.7020   0.6558
   2.000   0.3149   0.06320   0.05407  -0.0996   0.6977   0.6718
   2.250   0.3547   0.06381   0.05464  -0.1009   0.6916   0.6956
   2.500   0.3541   0.06593   0.05679  -0.1001   0.6904   0.7095
   2.750   0.3580   0.06791   0.05882  -0.0996   0.6897   0.7260
   3.000   0.3665   0.06983   0.06080  -0.0993   0.6903   0.7463
   3.250   0.2598   0.07772   0.06895  -0.0975   0.8172   0.7243
   3.500   0.2646   0.07838   0.06966  -0.0960   0.8079   0.7433
   3.750   0.2925   0.08032   0.07169  -0.0972   0.8002   0.7773
   4.000   0.2968   0.08107   0.07256  -0.0954   0.7918   0.8073
   4.250   0.3175   0.08215   0.07393  -0.0947   0.7826   0.8835
   4.500   0.3331   0.08321   0.07496  -0.0970   0.7706   1.0000
   4.750   0.3900   0.08771   0.07909  -0.1055   0.7634   1.0000
   5.000   0.3946   0.08860   0.07985  -0.1054   0.7511   1.0000
   5.250   0.4361   0.09270   0.08370  -0.1096   0.7448   1.0000
   5.500   0.4393   0.09345   0.08437  -0.1087   0.7318   1.0000
   5.750   0.4660   0.09681   0.08760  -0.1107   0.7261   1.0000
   6.000   0.4774   0.09825   0.08897  -0.1106   0.7133   1.0000
   6.250   0.4896   0.10058   0.09124  -0.1109   0.7050   1.0000
   6.500   0.5136   0.10315   0.09373  -0.1121   0.6948   1.0000
   6.750   0.5206   0.10527   0.09582  -0.1119   0.6864   1.0000
   7.000   0.5470   0.10811   0.09860  -0.1132   0.6767   1.0000
   7.250   0.5503   0.10996   0.10044  -0.1127   0.6668   1.0000
   7.500   0.5789   0.11319   0.10363  -0.1142   0.6586   1.0000
   7.750   0.5792   0.11495   0.10539  -0.1135   0.6492   1.0000
   8.000   0.6090   0.11833   0.10874  -0.1151   0.6407   1.0000
   8.250   0.6074   0.11994   0.11036  -0.1144   0.6305   1.0000
   8.500   0.6364   0.12347   0.11389  -0.1158   0.6231   1.0000
   8.750   0.6339   0.12513   0.11557  -0.1152   0.6135   1.0000
   9.000   0.6637   0.12875   0.11918  -0.1166   0.6054   1.0000
   9.250   0.6599   0.13032   0.12078  -0.1161   0.5957   1.0000
   9.500   0.6871   0.13391   0.12438  -0.1173   0.5881   1.0000
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