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

E392 (10.15%) (e392-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E392 (10.15%) (e392-il)
Reynolds number: 1,000,000
Max Cl/Cd: 146.6 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e392-il-1000000.txt
Download as CSV file: xf-e392-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E392  (10.15%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3314   0.09107   0.08950  -0.0375   1.0000   0.0098
  -8.750  -0.3303   0.08793   0.08638  -0.0383   1.0000   0.0101
  -8.500  -0.3309   0.08479   0.08328  -0.0390   1.0000   0.0102
  -8.250  -0.3278   0.08095   0.07946  -0.0413   0.9992   0.0106
  -8.000  -0.3158   0.07542   0.07394  -0.0475   0.9882   0.0111
  -7.750  -0.2984   0.06894   0.06746  -0.0565   0.9749   0.0114
  -7.500  -0.2655   0.05976   0.05824  -0.0732   0.9557   0.0117
  -7.000  -0.2436   0.04014   0.03799  -0.0946   0.8682   0.0118
  -6.750  -0.2544   0.03001   0.02719  -0.0982   0.8402   0.0123
  -6.500  -0.2376   0.02741   0.02435  -0.0986   0.8215   0.0125
  -6.250  -0.2263   0.01841   0.01420  -0.0985   0.8060   0.0087
  -6.000  -0.2028   0.01637   0.01186  -0.0983   0.7918   0.0083
  -5.750  -0.1779   0.01485   0.01000  -0.0981   0.7786   0.0084
  -5.500  -0.1536   0.01270   0.00745  -0.0978   0.7665   0.0089
  -5.250  -0.1276   0.01175   0.00635  -0.0977   0.7549   0.0092
  -5.000  -0.1007   0.01119   0.00569  -0.0976   0.7441   0.0096
  -4.750  -0.0737   0.01064   0.00503  -0.0975   0.7342   0.0099
  -4.250  -0.0190   0.00973   0.00391  -0.0974   0.7157   0.0105
  -4.000   0.0087   0.00942   0.00351  -0.0974   0.7074   0.0112
  -3.750   0.0366   0.00910   0.00312  -0.0974   0.6993   0.0116
  -3.500   0.0645   0.00872   0.00262  -0.0974   0.6921   0.0121
  -3.250   0.0926   0.00835   0.00217  -0.0974   0.6846   0.0138
  -3.000   0.1208   0.00817   0.00193  -0.0974   0.6779   0.0159
  -2.750   0.1490   0.00783   0.00165  -0.0975   0.6713   0.0350
  -2.500   0.1770   0.00760   0.00150  -0.0976   0.6650   0.0696
  -2.250   0.2053   0.00738   0.00140  -0.0978   0.6587   0.1078
  -2.000   0.2333   0.00719   0.00131  -0.0980   0.6528   0.1561
  -1.750   0.2614   0.00692   0.00123  -0.0982   0.6472   0.2254
  -1.500   0.2893   0.00656   0.00118  -0.0985   0.6413   0.3369
  -1.250   0.3172   0.00635   0.00116  -0.0987   0.6359   0.4197
  -1.000   0.3455   0.00618   0.00115  -0.0988   0.6305   0.4871
  -0.750   0.3735   0.00608   0.00115  -0.0989   0.6250   0.5405
  -0.500   0.4016   0.00597   0.00117  -0.0990   0.6199   0.5971
  -0.250   0.4297   0.00588   0.00118  -0.0991   0.6145   0.6421
   0.000   0.4574   0.00583   0.00121  -0.0990   0.6092   0.6886
   0.250   0.4852   0.00574   0.00124  -0.0990   0.6042   0.7374
   0.500   0.5123   0.00565   0.00128  -0.0987   0.5989   0.7908
   0.750   0.5379   0.00558   0.00133  -0.0981   0.5937   0.8478
   1.000   0.5610   0.00545   0.00137  -0.0969   0.5888   0.9129
   1.250   0.5922   0.00536   0.00134  -0.0974   0.5831   1.0000
   1.500   0.6204   0.00545   0.00137  -0.0975   0.5776   1.0000
   1.750   0.6490   0.00550   0.00140  -0.0977   0.5714   1.0000
   2.250   0.7054   0.00564   0.00148  -0.0979   0.5577   1.0000
   2.500   0.7334   0.00574   0.00154  -0.0979   0.5507   1.0000
   2.750   0.7617   0.00580   0.00160  -0.0980   0.5438   1.0000
   3.000   0.7895   0.00591   0.00166  -0.0981   0.5363   1.0000
   3.250   0.8176   0.00597   0.00173  -0.0982   0.5286   1.0000
   3.500   0.8452   0.00609   0.00181  -0.0982   0.5203   1.0000
   3.750   0.8732   0.00617   0.00189  -0.0982   0.5116   1.0000
   4.000   0.9009   0.00628   0.00199  -0.0982   0.5029   1.0000
   4.250   0.9283   0.00641   0.00209  -0.0982   0.4932   1.0000
   4.500   0.9558   0.00652   0.00221  -0.0982   0.4822   1.0000
   5.000   1.0088   0.00692   0.00247  -0.0979   0.4399   1.0000
   5.250   1.0349   0.00717   0.00265  -0.0977   0.4172   1.0000
   5.500   1.0595   0.00755   0.00287  -0.0973   0.3802   1.0000
   5.750   1.0828   0.00808   0.00319  -0.0967   0.3324   1.0000
   6.000   1.1043   0.00878   0.00361  -0.0959   0.2759   1.0000
   6.250   1.1254   0.00951   0.00408  -0.0951   0.2238   1.0000
   6.500   1.1465   0.01022   0.00455  -0.0942   0.1771   1.0000
   6.750   1.1670   0.01098   0.00507  -0.0933   0.1327   1.0000
   7.000   1.1869   0.01175   0.00561  -0.0922   0.0932   1.0000
   7.250   1.2061   0.01256   0.00621  -0.0911   0.0583   1.0000
   7.500   1.2229   0.01356   0.00697  -0.0896   0.0237   1.0000
   7.750   1.2428   0.01423   0.00759  -0.0884   0.0148   1.0000
   8.000   1.2640   0.01478   0.00818  -0.0874   0.0128   1.0000
   8.250   1.2856   0.01525   0.00870  -0.0866   0.0122   1.0000
   8.500   1.3062   0.01579   0.00930  -0.0855   0.0116   1.0000
   8.750   1.3256   0.01637   0.00993  -0.0844   0.0109   1.0000
   9.000   1.3430   0.01708   0.01069  -0.0829   0.0101   1.0000
   9.250   1.3566   0.01800   0.01171  -0.0808   0.0096   1.0000
   9.500   1.3667   0.01900   0.01282  -0.0782   0.0092   1.0000
   9.750   1.3787   0.01968   0.01356  -0.0758   0.0091   1.0000
  10.000   1.3891   0.02044   0.01438  -0.0733   0.0089   1.0000
  10.250   1.3976   0.02134   0.01537  -0.0707   0.0088   1.0000
  10.500   1.4053   0.02235   0.01646  -0.0681   0.0085   1.0000
  10.750   1.4126   0.02345   0.01763  -0.0658   0.0083   1.0000
  11.000   1.4191   0.02467   0.01894  -0.0636   0.0081   1.0000
  11.250   1.4266   0.02591   0.02025  -0.0617   0.0079   1.0000
  11.500   1.4341   0.02722   0.02163  -0.0601   0.0076   1.0000
  11.750   1.4390   0.02883   0.02332  -0.0584   0.0074   1.0000
  12.000   1.4434   0.03058   0.02513  -0.0569   0.0072   1.0000
  12.250   1.4451   0.03267   0.02730  -0.0554   0.0070   1.0000
  12.500   1.4453   0.03503   0.02977  -0.0541   0.0068   1.0000
  12.750   1.4377   0.03833   0.03318  -0.0526   0.0066   1.0000
  13.000   1.4289   0.04203   0.03704  -0.0510   0.0064   1.0000
  13.250   1.4347   0.04411   0.03921  -0.0505   0.0063   1.0000
  13.500   1.4409   0.04617   0.04138  -0.0502   0.0062   1.0000
  13.750   1.4445   0.04860   0.04390  -0.0499   0.0062   1.0000
  14.000   1.4467   0.05127   0.04669  -0.0497   0.0060   1.0000
  14.250   1.4493   0.05397   0.04950  -0.0497   0.0059   1.0000
  14.500   1.4513   0.05679   0.05242  -0.0499   0.0057   1.0000
  14.750   1.4509   0.06002   0.05577  -0.0501   0.0056   1.0000
  15.000   1.4490   0.06361   0.05947  -0.0505   0.0055   1.0000
  15.250   1.4486   0.06705   0.06302  -0.0513   0.0054   1.0000
  15.500   1.4469   0.07078   0.06685  -0.0522   0.0052   1.0000
  15.750   1.4443   0.07481   0.07100  -0.0533   0.0051   1.0000
  16.000   1.4404   0.07915   0.07546  -0.0546   0.0050   1.0000
  16.250   1.4354   0.08380   0.08024  -0.0562   0.0049   1.0000
  16.500   1.4291   0.08880   0.08535  -0.0580   0.0049   1.0000
  16.750   1.4233   0.09387   0.09054  -0.0601   0.0048   1.0000
  17.000   1.4173   0.09914   0.09591  -0.0625   0.0047   1.0000
  17.250   1.4099   0.10476   0.10164  -0.0651   0.0047   1.0000
  17.500   1.4006   0.11086   0.10786  -0.0680   0.0046   1.0000
  17.750   1.3910   0.11721   0.11433  -0.0712   0.0046   1.0000
  18.000   1.3800   0.12399   0.12123  -0.0748   0.0045   1.0000
  18.250   1.3682   0.13108   0.12846  -0.0787   0.0045   1.0000
  18.500   1.3549   0.13871   0.13622  -0.0832   0.0044   1.0000
  18.750   1.3411   0.14670   0.14435  -0.0880   0.0044   1.0000
  19.000   1.3274   0.15492   0.15271  -0.0931   0.0044   1.0000
<< Back to E392 (10.15%) (e392-il)

Polar data table (+)

Polar graphs


<< Back to E392 (10.15%) (e392-il)