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WORTMANN FX 74-080 (fx74080-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 74-080 (fx74080-il)
Reynolds number: 50,000
Max Cl/Cd: 27.06 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74080-il-50000-n5.txt
Download as CSV file: xf-fx74080-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 74-080                              
  
 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  -0.3980   0.11981   0.11368  -0.0360   1.0000   0.0699
  -8.250  -0.4116   0.11920   0.11317  -0.0342   1.0000   0.0700
  -8.000  -0.4281   0.11871   0.11279  -0.0323   1.0000   0.0702
  -7.750  -0.4037   0.11072   0.10477  -0.0296   1.0000   0.0739
  -7.500  -0.4111   0.10898   0.10310  -0.0276   1.0000   0.0753
  -7.250  -0.4192   0.10728   0.10146  -0.0260   0.9997   0.0766
  -7.000  -0.4155   0.10441   0.09863  -0.0290   0.9949   0.0800
  -6.750  -0.4091   0.10184   0.09608  -0.0387   0.9869   0.0831
  -6.500  -0.3982   0.09778   0.09203  -0.0435   0.9815   0.0843
  -6.250  -0.3866   0.09314   0.08740  -0.0404   0.9795   0.0884
  -6.000  -0.3754   0.08965   0.08389  -0.0447   0.9740   0.0940
  -5.750  -0.3609   0.08575   0.07995  -0.0523   0.9681   0.0983
  -5.500  -0.3459   0.08174   0.07592  -0.0524   0.9651   0.1036
  -5.000  -0.3170   0.07434   0.06841  -0.0590   0.9550   0.1172
  -4.750  -0.2959   0.07039   0.06435  -0.0637   0.9509   0.1280
  -4.250  -0.2268   0.05969   0.05290  -0.0752   0.9420   0.0545
  -4.000  -0.1859   0.05492   0.04753  -0.0805   0.9390   0.0430
  -3.750  -0.1692   0.05159   0.04411  -0.0810   0.9346   0.0409
  -3.500  -0.1409   0.04803   0.04021  -0.0833   0.9308   0.0389
  -3.250  -0.1071   0.04469   0.03626  -0.0861   0.9278   0.0381
  -3.000  -0.0708   0.04185   0.03279  -0.0887   0.9252   0.0412
  -2.750  -0.0436   0.04001   0.03026  -0.0888   0.9206   0.0433
  -2.500  -0.0132   0.03743   0.02725  -0.0900   0.9174   0.0445
  -2.250   0.0205   0.03530   0.02459  -0.0911   0.9148   0.0445
  -2.000   0.0554   0.03338   0.02225  -0.0924   0.9125   0.0457
  -1.750   0.0784   0.03221   0.02077  -0.0914   0.9081   0.0472
  -1.500   0.1058   0.03114   0.01940  -0.0910   0.9045   0.0507
  -1.250   0.1380   0.03029   0.01815  -0.0914   0.9016   0.0573
  -1.000   0.1704   0.02956   0.01731  -0.0926   0.8989   0.0789
  -0.750   0.1931   0.02891   0.01642  -0.0918   0.8939   0.1025
  -0.500   0.2193   0.02576   0.01599  -0.0912   0.8912   1.0000
  -0.250   0.2510   0.02613   0.01574  -0.0921   0.8875   1.0000
   0.000   0.2740   0.02655   0.01578  -0.0917   0.8823   1.0000
   0.250   0.2992   0.02697   0.01589  -0.0917   0.8773   1.0000
   0.500   0.3309   0.02738   0.01601  -0.0929   0.8737   1.0000
   0.750   0.3502   0.02787   0.01631  -0.0920   0.8676   1.0000
   1.000   0.3770   0.02833   0.01655  -0.0924   0.8630   1.0000
   1.250   0.4097   0.02878   0.01683  -0.0937   0.8597   1.0000
   1.500   0.4247   0.02936   0.01732  -0.0922   0.8526   1.0000
   1.750   0.4537   0.02985   0.01772  -0.0929   0.8484   1.0000
   2.000   0.4751   0.03042   0.01825  -0.0924   0.8427   1.0000
   2.250   0.4991   0.03098   0.01882  -0.0924   0.8372   1.0000
   2.500   0.5311   0.03146   0.01929  -0.0936   0.8335   1.0000
   2.750   0.5450   0.03217   0.02001  -0.0919   0.8258   1.0000
   3.000   0.5746   0.03269   0.02059  -0.0928   0.8215   1.0000
   3.250   0.5913   0.03341   0.02137  -0.0916   0.8143   1.0000
   3.500   0.6187   0.03398   0.02205  -0.0921   0.8092   1.0000
   3.750   0.6378   0.03469   0.02287  -0.0913   0.8023   1.0000
   4.000   0.6635   0.03529   0.02376  -0.0914   0.7964   1.0000
   4.250   0.6830   0.03602   0.02464  -0.0907   0.7891   1.0000
   4.500   0.7098   0.03658   0.02542  -0.0909   0.7828   1.0000
   4.750   0.7272   0.03735   0.02640  -0.0899   0.7744   1.0000
   5.000   0.7577   0.03783   0.02719  -0.0905   0.7686   1.0000
   5.250   0.7732   0.03863   0.02826  -0.0891   0.7587   1.0000
   5.500   0.7961   0.03925   0.02923  -0.0887   0.7503   1.0000
   5.750   0.8288   0.03925   0.02999  -0.0888   0.7400   1.0000
   6.250   0.8598   0.03177   0.01883  -0.0667   0.0658   1.0000
   6.500   0.8662   0.03374   0.02081  -0.0641   0.0548   1.0000
   6.750   0.8754   0.03547   0.02272  -0.0618   0.0465   1.0000
   7.000   0.8849   0.03727   0.02468  -0.0597   0.0383   1.0000
   7.250   0.8974   0.03900   0.02658  -0.0577   0.0342   1.0000
   7.500   0.9334   0.04093   0.02864  -0.0568   0.0312   1.0000
   7.750   1.0486   0.04512   0.03347  -0.0651   0.0289   1.0000
   8.000   1.0900   0.04906   0.03791  -0.0662   0.0286   1.0000
   8.250   1.1119   0.05241   0.04204  -0.0649   0.0271   1.0000
   8.500   1.1254   0.05557   0.04567  -0.0629   0.0254   1.0000
   8.750   1.1346   0.05878   0.04930  -0.0606   0.0245   1.0000
   9.000   1.1384   0.06197   0.05283  -0.0580   0.0231   1.0000
   9.250   1.1392   0.06537   0.05662  -0.0551   0.0230   1.0000
   9.500   1.1359   0.06863   0.06024  -0.0519   0.0231   1.0000
   9.750   1.1274   0.07197   0.06391  -0.0483   0.0234   1.0000
  10.000   1.1164   0.07528   0.06752  -0.0451   0.0238   1.0000
  10.250   1.1032   0.07874   0.07124  -0.0423   0.0241   1.0000
  10.500   1.0880   0.08244   0.07518  -0.0401   0.0244   1.0000
  10.750   1.0712   0.08643   0.07939  -0.0386   0.0246   1.0000
  11.000   1.0538   0.09067   0.08382  -0.0379   0.0249   1.0000
  11.250   1.0356   0.09536   0.08869  -0.0381   0.0252   1.0000
  11.500   1.0169   0.10052   0.09399  -0.0391   0.0253   1.0000
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