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E184 (8.33%) (e184-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E184 (8.33%) (e184-il)
Reynolds number: 100,000
Max Cl/Cd: 44.45 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e184-il-100000.txt
Download as CSV file: xf-e184-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E184  (8.33%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6281   0.10162   0.09739   0.0248   1.0000   0.1052
  -8.500  -0.6406   0.09757   0.09344   0.0189   1.0000   0.1094
  -8.250  -0.6675   0.09325   0.08919   0.0091   1.0000   0.1106
  -8.000  -0.6380   0.08846   0.08443   0.0152   1.0000   0.1147
  -7.750  -0.6358   0.08468   0.08068   0.0135   1.0000   0.1191
  -7.250  -0.6374   0.07511   0.07110   0.0061   1.0000   0.1288
  -7.000  -0.5673   0.06127   0.05763   0.0022   1.0000   0.1424
  -6.500  -0.6191   0.06205   0.05780  -0.0011   1.0000   0.1547
  -6.250  -0.6082   0.05833   0.05393  -0.0025   1.0000   0.1679
  -5.750  -0.5699   0.03836   0.03183  -0.0061   1.0000   0.0692
  -5.500  -0.5483   0.03442   0.02756  -0.0060   1.0000   0.0679
  -5.250  -0.5247   0.03096   0.02368  -0.0057   1.0000   0.0667
  -5.000  -0.4993   0.02763   0.01985  -0.0054   1.0000   0.0639
  -4.750  -0.4728   0.02493   0.01664  -0.0051   1.0000   0.0625
  -4.500  -0.4480   0.02290   0.01430  -0.0046   1.0000   0.0628
  -4.250  -0.4308   0.02146   0.01270  -0.0031   1.0000   0.0642
  -4.000  -0.4175   0.02034   0.01144  -0.0009   1.0000   0.0663
  -3.750  -0.3880   0.01894   0.00997  -0.0017   0.9937   0.0730
  -3.500  -0.3454   0.01738   0.00850  -0.0048   0.9836   0.0880
  -3.250  -0.3108   0.01486   0.00681  -0.0064   0.9731   0.2089
  -3.000  -0.2849   0.01259   0.00658  -0.0065   0.9627   0.6050
  -2.750  -0.1834   0.01253   0.00709  -0.0155   0.9762   0.9483
  -2.500  -0.0881   0.01238   0.00646  -0.0279   0.9848   1.0000
  -2.250  -0.0430   0.01231   0.00610  -0.0325   0.9648   1.0000
  -2.000  -0.0044   0.01230   0.00583  -0.0355   0.9473   1.0000
  -1.750   0.0239   0.01240   0.00573  -0.0361   0.9304   1.0000
  -1.500   0.0461   0.01256   0.00573  -0.0355   0.9149   1.0000
  -1.250   0.0668   0.01274   0.00578  -0.0344   0.9009   1.0000
  -1.000   0.0872   0.01293   0.00583  -0.0332   0.8883   1.0000
  -0.750   0.1083   0.01312   0.00592  -0.0322   0.8763   1.0000
  -0.500   0.1301   0.01333   0.00604  -0.0313   0.8651   1.0000
  -0.250   0.1517   0.01356   0.00619  -0.0303   0.8548   1.0000
   0.000   0.1721   0.01380   0.00635  -0.0289   0.8454   1.0000
   0.250   0.1951   0.01404   0.00654  -0.0282   0.8353   1.0000
   0.500   0.2181   0.01430   0.00676  -0.0275   0.8256   1.0000
   0.750   0.2394   0.01456   0.00698  -0.0262   0.8169   1.0000
   1.000   0.2624   0.01483   0.00725  -0.0254   0.8071   1.0000
   1.250   0.2857   0.01512   0.00754  -0.0247   0.7972   1.0000
   1.500   0.3072   0.01538   0.00779  -0.0233   0.7881   1.0000
   1.750   0.3290   0.01562   0.00803  -0.0220   0.7781   1.0000
   2.000   0.3520   0.01589   0.00834  -0.0211   0.7669   1.0000
   2.250   0.3743   0.01615   0.00865  -0.0198   0.7559   1.0000
   2.500   0.3955   0.01634   0.00887  -0.0182   0.7450   1.0000
   2.750   0.4157   0.01645   0.00900  -0.0160   0.7342   1.0000
   3.000   0.4376   0.01659   0.00919  -0.0144   0.7214   1.0000
   3.250   0.4594   0.01670   0.00940  -0.0127   0.7080   1.0000
   3.500   0.4808   0.01673   0.00949  -0.0108   0.6940   1.0000
   3.750   0.5020   0.01669   0.00951  -0.0086   0.6793   1.0000
   4.000   0.5234   0.01658   0.00946  -0.0064   0.6640   1.0000
   4.250   0.5460   0.01650   0.00951  -0.0047   0.6446   1.0000
   4.500   0.5677   0.01622   0.00935  -0.0024   0.6253   1.0000
   4.750   0.5899   0.01592   0.00915  -0.0002   0.6027   1.0000
   5.000   0.6124   0.01553   0.00886   0.0020   0.5761   1.0000
   5.250   0.6351   0.01512   0.00856   0.0041   0.5405   1.0000
   5.500   0.6578   0.01480   0.00828   0.0061   0.4814   1.0000
   5.750   0.6753   0.01560   0.00821   0.0079   0.3011   1.0000
   6.000   0.6874   0.01880   0.01000   0.0083   0.1146   1.0000
   6.250   0.7018   0.02157   0.01232   0.0099   0.0648   1.0000
   6.500   0.7198   0.02359   0.01422   0.0116   0.0555   1.0000
   6.750   0.7412   0.02510   0.01580   0.0128   0.0489   1.0000
   7.000   0.7617   0.02747   0.01812   0.0140   0.0444   1.0000
   7.250   0.7849   0.02968   0.02064   0.0153   0.0429   1.0000
   7.500   0.8070   0.03236   0.02366   0.0166   0.0423   1.0000
   7.750   0.8268   0.03548   0.02718   0.0178   0.0424   1.0000
   8.000   0.8436   0.03905   0.03118   0.0189   0.0430   1.0000
   8.250   0.8570   0.04316   0.03569   0.0200   0.0440   1.0000
   8.500   0.8691   0.04839   0.04116   0.0207   0.0455   1.0000
   8.750   0.8670   0.05252   0.04638   0.0227   0.0514   1.0000
   9.000   0.8085   0.04661   0.04114   0.0253   0.0533   1.0000
   9.250   0.8167   0.05213   0.04674   0.0260   0.0586   1.0000
   9.500   0.7785   0.05646   0.05146   0.0268   0.0601   1.0000
   9.750   0.7490   0.06100   0.05614   0.0261   0.0605   1.0000
  10.000   0.7211   0.06652   0.06176   0.0238   0.0606   1.0000
  10.250   0.6931   0.07332   0.06862   0.0200   0.0605   1.0000
  10.500   0.6602   0.08261   0.07795   0.0140   0.0610   1.0000
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