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E174 (Dicke 8.92%) (e174-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E174 (Dicke 8.92%) (e174-il)
Reynolds number: 50,000
Max Cl/Cd: 39.04 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e174-il-50000-n5.txt
Download as CSV file: xf-e174-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E174  (Dicke 8.92%)                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3446   0.10405   0.09738  -0.0280   1.0000   0.1006
  -8.250  -0.3549   0.10276   0.09626  -0.0315   1.0000   0.1038
  -8.000  -0.3627   0.10087   0.09451  -0.0340   1.0000   0.1043
  -7.750  -0.3522   0.09634   0.09006  -0.0332   1.0000   0.1056
  -7.500  -0.3389   0.09249   0.08623  -0.0317   1.0000   0.1085
  -7.250  -0.3376   0.08984   0.08368  -0.0316   1.0000   0.1111
  -7.000  -0.3387   0.08457   0.07847  -0.0358   1.0000   0.0716
  -6.500  -0.3453   0.07540   0.06943  -0.0448   1.0000   0.0501
  -6.250  -0.3473   0.07286   0.06698  -0.0435   1.0000   0.0496
  -6.000  -0.3515   0.07055   0.06474  -0.0422   1.0000   0.0491
  -5.750  -0.3448   0.06717   0.06135  -0.0439   0.9960   0.0484
  -5.500  -0.3134   0.06159   0.05560  -0.0515   0.9840   0.0469
  -5.250  -0.2802   0.05577   0.04953  -0.0591   0.9723   0.0452
  -5.000  -0.2465   0.05001   0.04336  -0.0659   0.9605   0.0436
  -4.750  -0.2115   0.04458   0.03742  -0.0717   0.9496   0.0424
  -4.500  -0.1740   0.03982   0.03204  -0.0766   0.9407   0.0417
  -4.250  -0.1370   0.03591   0.02749  -0.0801   0.9316   0.0419
  -4.000  -0.1019   0.03294   0.02394  -0.0824   0.9222   0.0430
  -3.750  -0.0634   0.03045   0.02085  -0.0848   0.9148   0.0471
  -3.500  -0.0302   0.02848   0.01820  -0.0856   0.9047   0.0505
  -3.250   0.0034   0.02663   0.01619  -0.0867   0.8965   0.0542
  -3.000   0.0364   0.02524   0.01449  -0.0873   0.8877   0.0612
  -2.750   0.0673   0.02416   0.01320  -0.0876   0.8783   0.0757
  -2.500   0.1014   0.02296   0.01204  -0.0888   0.8708   0.1116
  -2.250   0.1295   0.02179   0.01118  -0.0892   0.8609   0.1927
  -2.000   0.1578   0.02048   0.01065  -0.0896   0.8527   0.3644
  -1.750   0.1757   0.01927   0.01055  -0.0868   0.8439   0.6420
  -1.500   0.2209   0.01853   0.00992  -0.0885   0.8367   1.0000
  -1.250   0.2504   0.01868   0.00961  -0.0888   0.8281   1.0000
  -1.000   0.2765   0.01892   0.00948  -0.0886   0.8185   1.0000
  -0.750   0.3062   0.01908   0.00928  -0.0888   0.8111   1.0000
  -0.500   0.3313   0.01936   0.00930  -0.0885   0.8015   1.0000
  -0.250   0.3585   0.01961   0.00929  -0.0884   0.7935   1.0000
   0.000   0.3856   0.01987   0.00933  -0.0883   0.7854   1.0000
   0.250   0.4116   0.02018   0.00945  -0.0882   0.7770   1.0000
   0.500   0.4394   0.02044   0.00953  -0.0881   0.7699   1.0000
   0.750   0.4644   0.02081   0.00978  -0.0878   0.7613   1.0000
   1.000   0.4923   0.02107   0.00990  -0.0877   0.7546   1.0000
   1.250   0.5165   0.02150   0.01025  -0.0874   0.7461   1.0000
   1.500   0.5445   0.02176   0.01042  -0.0873   0.7397   1.0000
   1.750   0.5680   0.02225   0.01087  -0.0869   0.7310   1.0000
   2.000   0.5960   0.02252   0.01109  -0.0868   0.7249   1.0000
   2.250   0.6189   0.02306   0.01164  -0.0863   0.7161   1.0000
   2.500   0.6469   0.02333   0.01187  -0.0861   0.7101   1.0000
   2.750   0.6691   0.02393   0.01251  -0.0856   0.7011   1.0000
   3.000   0.6974   0.02419   0.01280  -0.0854   0.6952   1.0000
   3.250   0.7188   0.02484   0.01352  -0.0849   0.6858   1.0000
   3.500   0.7466   0.02512   0.01383  -0.0846   0.6796   1.0000
   3.750   0.7682   0.02577   0.01458  -0.0840   0.6701   1.0000
   4.000   0.7930   0.02622   0.01515  -0.0835   0.6622   1.0000
   4.250   0.8178   0.02663   0.01567  -0.0829   0.6538   1.0000
   4.500   0.8400   0.02721   0.01638  -0.0822   0.6439   1.0000
   4.750   0.8690   0.02730   0.01656  -0.0817   0.6367   1.0000
   5.000   0.8897   0.02791   0.01738  -0.0808   0.6251   1.0000
   5.250   0.9120   0.02837   0.01801  -0.0798   0.6139   1.0000
   5.500   0.9364   0.02863   0.01844  -0.0789   0.6028   1.0000
   5.750   0.9629   0.02865   0.01862  -0.0779   0.5916   1.0000
   6.000   0.9883   0.02868   0.01889  -0.0768   0.5790   1.0000
   6.250   1.0118   0.02876   0.01918  -0.0755   0.5646   1.0000
   6.500   1.0325   0.02897   0.01962  -0.0740   0.5479   1.0000
   6.750   1.0530   0.02909   0.01999  -0.0723   0.5295   1.0000
   7.000   1.0760   0.02889   0.02005  -0.0706   0.5098   1.0000
   7.250   1.0949   0.02894   0.02034  -0.0686   0.4863   1.0000
   7.500   1.1135   0.02893   0.02054  -0.0665   0.4590   1.0000
   7.750   1.1302   0.02900   0.02079  -0.0641   0.4253   1.0000
   8.000   1.1436   0.02929   0.02112  -0.0615   0.3817   1.0000
   8.250   1.1523   0.03000   0.02170  -0.0585   0.3255   1.0000
   8.500   1.1535   0.03152   0.02281  -0.0553   0.2652   1.0000
   8.750   1.1471   0.03373   0.02458  -0.0520   0.2132   1.0000
   9.000   1.1380   0.03634   0.02682  -0.0492   0.1702   1.0000
   9.250   1.1296   0.03927   0.02943  -0.0472   0.1322   1.0000
   9.500   1.1231   0.04234   0.03227  -0.0458   0.1046   1.0000
   9.750   1.1194   0.04542   0.03527  -0.0446   0.0847   1.0000
  10.000   1.1163   0.04858   0.03838  -0.0436   0.0720   1.0000
  10.250   1.1149   0.05169   0.04148  -0.0426   0.0627   1.0000
  10.500   1.1139   0.05481   0.04457  -0.0419   0.0560   1.0000
  10.750   1.1195   0.05735   0.04730  -0.0409   0.0503   1.0000
  11.000   1.1229   0.06013   0.05011  -0.0402   0.0464   1.0000
  11.250   1.1332   0.06241   0.05262  -0.0388   0.0436   1.0000
  11.500   1.1496   0.06444   0.05495  -0.0370   0.0409   1.0000
  11.750   1.1656   0.06672   0.05750  -0.0356   0.0389   1.0000
  12.000   1.1771   0.06953   0.06054  -0.0346   0.0375   1.0000
  12.250   1.1846   0.07268   0.06386  -0.0340   0.0361   1.0000
  12.500   1.1888   0.07646   0.06781  -0.0337   0.0351   1.0000
  12.750   1.1828   0.08101   0.07273  -0.0343   0.0345   1.0000
  13.000   1.1729   0.08613   0.07821  -0.0355   0.0341   1.0000
  13.250   1.1610   0.09168   0.08405  -0.0373   0.0339   1.0000
  13.500   1.1467   0.09775   0.09040  -0.0397   0.0338   1.0000
  13.750   1.1308   0.10439   0.09728  -0.0428   0.0338   1.0000
  14.000   1.1134   0.11165   0.10475  -0.0466   0.0339   1.0000
  14.250   1.0955   0.11962   0.11289  -0.0512   0.0342   1.0000
  14.500   1.0791   0.12799   0.12141  -0.0562   0.0345   1.0000
  14.750   1.0638   0.13681   0.13033  -0.0616   0.0348   1.0000
  15.000   1.0505   0.14589   0.13948  -0.0672   0.0351   1.0000
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