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E174 (Dicke 8.92%) (e174-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E174 (Dicke 8.92%) (e174-il)
Reynolds number: 200,000
Max Cl/Cd: 84.88 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e174-il-200000.txt
Download as CSV file: xf-e174-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3300   0.08652   0.08329  -0.0342   1.0000   0.0403
  -7.500  -0.3358   0.08418   0.08104  -0.0360   1.0000   0.0409
  -7.250  -0.3404   0.08141   0.07838  -0.0408   1.0000   0.0414
  -7.000  -0.3462   0.07885   0.07591  -0.0425   1.0000   0.0415
  -6.750  -0.3294   0.07403   0.07105  -0.0511   0.9934   0.0418
  -6.500  -0.3155   0.06779   0.06488  -0.0520   0.9869   0.0432
  -6.250  -0.2879   0.06418   0.06126  -0.0553   0.9790   0.0452
  -5.500  -0.1781   0.04549   0.04197  -0.0848   0.9435   0.0564
  -5.250  -0.1511   0.04294   0.03934  -0.0869   0.9295   0.0615
  -5.000  -0.1240   0.03823   0.03422  -0.0910   0.9138   0.0697
  -4.750  -0.1020   0.03605   0.03194  -0.0912   0.8989   0.0739
  -4.500  -0.0785   0.03275   0.02817  -0.0924   0.8843   0.0833
  -4.250  -0.0562   0.03066   0.02596  -0.0922   0.8710   0.0875
  -4.000  -0.0224   0.02153   0.01532  -0.0915   0.8601   0.0372
  -3.750   0.0049   0.01865   0.01167  -0.0905   0.8492   0.0328
  -3.500   0.0316   0.01723   0.00990  -0.0897   0.8391   0.0324
  -3.250   0.0578   0.01586   0.00833  -0.0890   0.8287   0.0330
  -3.000   0.0840   0.01491   0.00730  -0.0885   0.8185   0.0355
  -2.750   0.1107   0.01438   0.00663  -0.0880   0.8097   0.0402
  -2.500   0.1368   0.01339   0.00558  -0.0874   0.8004   0.0448
  -2.250   0.1637   0.01267   0.00484  -0.0870   0.7917   0.0612
  -2.000   0.1895   0.01161   0.00432  -0.0869   0.7840   0.1988
  -1.750   0.2136   0.01074   0.00429  -0.0867   0.7753   0.4226
  -1.500   0.2333   0.00991   0.00428  -0.0848   0.7686   0.6800
  -1.250   0.2715   0.00923   0.00410  -0.0855   0.7605   0.9872
  -1.000   0.3005   0.00934   0.00394  -0.0856   0.7540   1.0000
  -0.750   0.3274   0.00944   0.00389  -0.0855   0.7456   1.0000
  -0.500   0.3545   0.00957   0.00380  -0.0852   0.7395   1.0000
  -0.250   0.3815   0.00969   0.00382  -0.0851   0.7315   1.0000
   0.000   0.4088   0.00983   0.00378  -0.0849   0.7255   1.0000
   0.250   0.4358   0.00996   0.00383  -0.0848   0.7179   1.0000
   0.500   0.4632   0.01010   0.00383  -0.0846   0.7119   1.0000
   0.750   0.4903   0.01025   0.00392  -0.0845   0.7049   1.0000
   1.000   0.5176   0.01039   0.00397  -0.0843   0.6986   1.0000
   1.250   0.5449   0.01056   0.00408  -0.0842   0.6923   1.0000
   1.500   0.5721   0.01071   0.00417  -0.0841   0.6856   1.0000
   1.750   0.5995   0.01088   0.00427  -0.0840   0.6799   1.0000
   2.000   0.6265   0.01104   0.00444  -0.0839   0.6727   1.0000
   2.250   0.6541   0.01121   0.00453  -0.0837   0.6673   1.0000
   2.500   0.6809   0.01139   0.00474  -0.0836   0.6598   1.0000
   2.750   0.7083   0.01154   0.00484  -0.0834   0.6538   1.0000
   3.000   0.7351   0.01172   0.00507  -0.0833   0.6462   1.0000
   3.250   0.7623   0.01185   0.00517  -0.0831   0.6395   1.0000
   3.500   0.7889   0.01201   0.00537  -0.0828   0.6311   1.0000
   3.750   0.8162   0.01213   0.00543  -0.0826   0.6240   1.0000
   4.000   0.8424   0.01225   0.00566  -0.0823   0.6144   1.0000
   4.250   0.8692   0.01237   0.00579  -0.0819   0.6061   1.0000
   4.500   0.8958   0.01246   0.00591  -0.0816   0.5969   1.0000
   4.750   0.9220   0.01257   0.00611  -0.0812   0.5868   1.0000
   5.000   0.9484   0.01265   0.00623  -0.0808   0.5768   1.0000
   5.250   0.9749   0.01271   0.00630  -0.0804   0.5663   1.0000
   5.500   1.0005   0.01277   0.00647  -0.0799   0.5539   1.0000
   5.750   1.0260   0.01283   0.00663  -0.0793   0.5404   1.0000
   6.000   1.0509   0.01283   0.00666  -0.0786   0.5228   1.0000
   6.250   1.0746   0.01283   0.00671  -0.0776   0.4971   1.0000
   6.500   1.0975   0.01293   0.00680  -0.0766   0.4655   1.0000
   6.750   1.1190   0.01320   0.00702  -0.0754   0.4203   1.0000
   7.000   1.1387   0.01374   0.00739  -0.0741   0.3653   1.0000
   7.250   1.1519   0.01492   0.00810  -0.0722   0.2779   1.0000
   7.500   1.1633   0.01640   0.00913  -0.0702   0.2012   1.0000
   7.750   1.1709   0.01827   0.01044  -0.0679   0.1163   1.0000
   8.000   1.1710   0.02083   0.01239  -0.0646   0.0447   1.0000
   8.250   1.1800   0.02241   0.01398  -0.0621   0.0351   1.0000
   8.500   1.1917   0.02364   0.01533  -0.0599   0.0315   1.0000
   8.750   1.1998   0.02497   0.01675  -0.0574   0.0294   1.0000
   9.000   1.2010   0.02666   0.01849  -0.0541   0.0279   1.0000
   9.250   1.2021   0.02864   0.02053  -0.0511   0.0270   1.0000
   9.500   1.2116   0.03016   0.02215  -0.0490   0.0264   1.0000
   9.750   1.2229   0.03180   0.02390  -0.0472   0.0257   1.0000
  10.000   1.2363   0.03340   0.02564  -0.0457   0.0248   1.0000
  10.250   1.2502   0.03501   0.02736  -0.0444   0.0237   1.0000
  10.500   1.2657   0.03682   0.02929  -0.0432   0.0229   1.0000
  10.750   1.2841   0.03896   0.03158  -0.0422   0.0224   1.0000
  11.000   1.3021   0.04141   0.03424  -0.0412   0.0221   1.0000
  11.250   1.3179   0.04429   0.03739  -0.0401   0.0221   1.0000
  11.500   1.3277   0.04766   0.04111  -0.0386   0.0224   1.0000
  11.750   1.3277   0.05149   0.04535  -0.0367   0.0229   1.0000
  12.000   1.3206   0.05563   0.04987  -0.0348   0.0234   1.0000
  12.250   1.3093   0.05999   0.05457  -0.0333   0.0240   1.0000
  12.500   1.2957   0.06458   0.05945  -0.0323   0.0245   1.0000
  12.750   1.2800   0.06944   0.06457  -0.0321   0.0250   1.0000
  13.000   1.2624   0.07467   0.07004  -0.0325   0.0254   1.0000
  13.250   1.2436   0.08031   0.07589  -0.0336   0.0258   1.0000
  13.500   1.2237   0.08646   0.08224  -0.0354   0.0261   1.0000
  13.750   1.2035   0.09323   0.08917  -0.0378   0.0265   1.0000
  14.000   1.0372   0.09648   0.09295  -0.0360   0.0253   1.0000
  14.250   1.0070   0.10349   0.10016  -0.0401   0.0255   1.0000
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