Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EPPLER 793 AIRFOIL (e793-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 793 AIRFOIL (e793-il)
Reynolds number: 100,000
Max Cl/Cd: 52.37 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e793-il-100000-n5.txt
Download as CSV file: xf-e793-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 793 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3840   0.09663   0.09133  -0.0530   1.0000   0.0356
 -11.250  -0.4674   0.07601   0.07064  -0.0645   1.0000   0.0343
 -11.000  -0.5386   0.06266   0.05705  -0.0735   1.0000   0.0333
 -10.750  -0.5783   0.05644   0.05066  -0.0765   1.0000   0.0330
 -10.500  -0.6109   0.05274   0.04686  -0.0763   1.0000   0.0328
 -10.250  -0.6437   0.05016   0.04422  -0.0742   1.0000   0.0327
 -10.000  -0.6624   0.04778   0.04171  -0.0724   1.0000   0.0328
  -9.750  -0.6544   0.04468   0.03836  -0.0748   0.9953   0.0331
  -9.500  -0.6304   0.04148   0.03486  -0.0790   0.9871   0.0336
  -9.250  -0.6046   0.03874   0.03182  -0.0823   0.9792   0.0343
  -9.000  -0.5763   0.03635   0.02915  -0.0852   0.9716   0.0353
  -8.750  -0.5503   0.03426   0.02669  -0.0871   0.9622   0.0367
  -8.500  -0.5213   0.03259   0.02495  -0.0890   0.9543   0.0379
  -8.250  -0.4908   0.03112   0.02343  -0.0908   0.9463   0.0393
  -8.000  -0.4624   0.02971   0.02189  -0.0920   0.9372   0.0407
  -7.750  -0.4288   0.02827   0.02030  -0.0939   0.9306   0.0423
  -7.500  -0.4008   0.02704   0.01896  -0.0947   0.9208   0.0439
  -7.250  -0.3658   0.02579   0.01771  -0.0970   0.9146   0.0465
  -7.000  -0.3369   0.02479   0.01658  -0.0978   0.9042   0.0500
  -6.750  -0.3000   0.02359   0.01535  -0.1004   0.8978   0.0548
  -6.500  -0.2712   0.02257   0.01426  -0.1012   0.8865   0.0606
  -6.250  -0.2366   0.02145   0.01308  -0.1032   0.8782   0.0707
  -6.000  -0.2049   0.02039   0.01207  -0.1046   0.8676   0.0901
  -5.750  -0.1729   0.01946   0.01121  -0.1060   0.8569   0.1191
  -5.500  -0.1371   0.01862   0.01047  -0.1080   0.8477   0.1574
  -5.250  -0.1071   0.01806   0.01007  -0.1088   0.8352   0.2030
  -5.000  -0.0746   0.01771   0.00977  -0.1099   0.8236   0.2460
  -4.750  -0.0398   0.01747   0.00942  -0.1111   0.8130   0.2756
  -4.500  -0.0104   0.01732   0.00922  -0.1113   0.7998   0.2970
  -4.250   0.0199   0.01720   0.00901  -0.1116   0.7871   0.3174
  -4.000   0.0509   0.01709   0.00879  -0.1120   0.7751   0.3364
  -3.750   0.0815   0.01699   0.00858  -0.1122   0.7631   0.3536
  -3.500   0.1098   0.01692   0.00841  -0.1121   0.7499   0.3689
  -3.250   0.1387   0.01685   0.00824  -0.1121   0.7375   0.3834
  -3.000   0.1683   0.01678   0.00804  -0.1122   0.7260   0.3977
  -2.750   0.1963   0.01673   0.00787  -0.1120   0.7136   0.4112
  -2.500   0.2237   0.01668   0.00778  -0.1117   0.7013   0.4233
  -2.250   0.2520   0.01664   0.00765  -0.1116   0.6903   0.4357
  -2.000   0.2800   0.01662   0.00751  -0.1114   0.6788   0.4487
  -1.750   0.3068   0.01661   0.00746  -0.1110   0.6671   0.4607
  -1.500   0.3346   0.01660   0.00737  -0.1108   0.6568   0.4727
  -1.250   0.3618   0.01661   0.00730  -0.1105   0.6459   0.4857
  -1.000   0.3887   0.01663   0.00727  -0.1102   0.6352   0.4988
  -0.500   0.4424   0.01669   0.00725  -0.1094   0.6152   0.5246
  -0.250   0.4695   0.01674   0.00724  -0.1091   0.6061   0.5389
   0.000   0.4960   0.01680   0.00727  -0.1087   0.5963   0.5539
   0.250   0.5225   0.01687   0.00731  -0.1083   0.5874   0.5688
   0.500   0.5487   0.01694   0.00737  -0.1078   0.5784   0.5843
   0.750   0.5748   0.01702   0.00746  -0.1073   0.5697   0.6004
   1.000   0.6008   0.01711   0.00753  -0.1068   0.5613   0.6176
   1.250   0.6267   0.01722   0.00764  -0.1063   0.5529   0.6357
   1.500   0.6526   0.01732   0.00774  -0.1058   0.5448   0.6549
   1.750   0.6782   0.01744   0.00788  -0.1052   0.5370   0.6754
   2.000   0.7030   0.01755   0.00802  -0.1045   0.5291   0.6966
   2.250   0.7280   0.01767   0.00815  -0.1037   0.5220   0.7201
   2.500   0.7516   0.01778   0.00834  -0.1027   0.5141   0.7460
   2.750   0.7757   0.01788   0.00843  -0.1017   0.5079   0.7749
   3.000   0.7966   0.01798   0.00866  -0.1002   0.5001   0.8087
   3.250   0.8176   0.01801   0.00876  -0.0984   0.4937   0.8522
   3.500   0.8433   0.01804   0.00887  -0.0978   0.4868   0.9298
   3.750   0.8732   0.01826   0.00905  -0.0984   0.4794   1.0000
   4.000   0.9012   0.01855   0.00923  -0.0986   0.4734   1.0000
   4.250   0.9268   0.01888   0.00956  -0.0984   0.4660   1.0000
   4.500   0.9538   0.01918   0.00978  -0.0984   0.4599   1.0000
   4.750   0.9793   0.01952   0.01012  -0.0982   0.4533   1.0000
   5.000   1.0047   0.01986   0.01044  -0.0979   0.4467   1.0000
   5.500   1.0552   0.02058   0.01115  -0.0973   0.4344   1.0000
   5.750   1.0803   0.02093   0.01148  -0.0970   0.4284   1.0000
   6.000   1.1057   0.02131   0.01183  -0.0967   0.4229   1.0000
   6.250   1.1286   0.02173   0.01233  -0.0960   0.4163   1.0000
   6.500   1.1535   0.02210   0.01268  -0.0956   0.4108   1.0000
   6.750   1.1770   0.02253   0.01314  -0.0951   0.4050   1.0000
   7.000   1.1992   0.02298   0.01366  -0.0943   0.3987   1.0000
   7.250   1.2238   0.02337   0.01403  -0.0939   0.3935   1.0000
   7.500   1.2451   0.02386   0.01460  -0.0930   0.3876   1.0000
   7.750   1.2664   0.02433   0.01513  -0.0922   0.3813   1.0000
   8.000   1.2906   0.02473   0.01551  -0.0917   0.3763   1.0000
   8.250   1.3085   0.02530   0.01622  -0.0903   0.3697   1.0000
   8.500   1.3288   0.02576   0.01673  -0.0893   0.3636   1.0000
   8.750   1.3502   0.02622   0.01721  -0.0885   0.3581   1.0000
   9.000   1.3658   0.02683   0.01796  -0.0868   0.3513   1.0000
   9.250   1.3855   0.02728   0.01843  -0.0857   0.3455   1.0000
   9.500   1.4008   0.02790   0.01916  -0.0840   0.3393   1.0000
   9.750   1.4149   0.02849   0.01985  -0.0822   0.3328   1.0000
  10.000   1.4328   0.02895   0.02029  -0.0808   0.3273   1.0000
  10.250   1.4395   0.02976   0.02128  -0.0780   0.3205   1.0000
  10.500   1.4524   0.03036   0.02193  -0.0761   0.3143   1.0000
  10.750   1.4620   0.03116   0.02283  -0.0738   0.3081   1.0000
  11.000   1.4691   0.03204   0.02383  -0.0714   0.3014   1.0000
  11.250   1.4813   0.03276   0.02455  -0.0697   0.2955   1.0000
  11.500   1.4831   0.03401   0.02600  -0.0671   0.2885   1.0000
  11.750   1.4915   0.03496   0.02698  -0.0652   0.2823   1.0000
  12.000   1.4935   0.03638   0.02856  -0.0631   0.2756   1.0000
  12.250   1.4965   0.03778   0.03006  -0.0612   0.2689   1.0000
  12.500   1.4997   0.03929   0.03165  -0.0595   0.2625   1.0000
  12.750   1.4977   0.04126   0.03377  -0.0578   0.2553   1.0000
  13.000   1.5009   0.04292   0.03545  -0.0565   0.2489   1.0000
  13.250   1.4948   0.04554   0.03826  -0.0552   0.2416   1.0000
  13.500   1.4970   0.04745   0.04017  -0.0542   0.2350   1.0000
  13.750   1.4872   0.05079   0.04372  -0.0535   0.2277   1.0000
  14.000   1.4862   0.05322   0.04617  -0.0529   0.2209   1.0000
  14.250   1.4745   0.05715   0.05028  -0.0528   0.2136   1.0000
  14.500   1.4708   0.06016   0.05332  -0.0527   0.2067   1.0000
  14.750   1.4577   0.06465   0.05798  -0.0532   0.1995   1.0000
  15.000   1.4523   0.06818   0.06153  -0.0535   0.1926   1.0000
  15.250   1.4387   0.07315   0.06665  -0.0545   0.1855   1.0000
  15.500   1.4324   0.07708   0.07061  -0.0553   0.1787   1.0000
  15.750   1.4192   0.08232   0.07599  -0.0567   0.1719   1.0000
  16.000   1.4120   0.08666   0.08036  -0.0578   0.1653   1.0000
  16.250   1.4013   0.09175   0.08555  -0.0594   0.1589   1.0000
  16.500   1.3930   0.09653   0.09040  -0.0610   0.1526   1.0000
<< Back to EPPLER 793 AIRFOIL (e793-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER 793 AIRFOIL (e793-il)