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WORTMANN FX 74-080 (fx74080-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 74-080 (fx74080-il)
Reynolds number: 1,000,000
Max Cl/Cd: 164.5 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74080-il-1000000-n5.txt
Download as CSV file: xf-fx74080-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.1667   0.08302   0.08050  -0.0892   0.8143   0.0032
  -8.250  -0.1560   0.07975   0.07723  -0.0920   0.8123   0.0032
  -8.000  -0.1500   0.07549   0.07297  -0.0949   0.8102   0.0029
  -7.750  -0.1413   0.07148   0.06896  -0.0986   0.8081   0.0027
  -7.500  -0.1313   0.06785   0.06533  -0.1024   0.8063   0.0026
  -7.250  -0.1207   0.06431   0.06180  -0.1069   0.8044   0.0026
  -7.000  -0.1070   0.05974   0.05723  -0.1133   0.8022   0.0025
  -6.750  -0.0917   0.05507   0.05253  -0.1192   0.8000   0.0024
  -6.500  -0.0746   0.05112   0.04853  -0.1238   0.7981   0.0023
  -6.250  -0.0571   0.04620   0.04352  -0.1284   0.7959   0.0023
  -6.000  -0.0386   0.04147   0.03866  -0.1319   0.7935   0.0023
  -5.750  -0.0200   0.03670   0.03376  -0.1341   0.7908   0.0023
  -5.500  -0.0010   0.03121   0.02804  -0.1354   0.7882   0.0026
  -5.000   0.0398   0.02253   0.01881  -0.1353   0.7840   0.0038
  -4.750   0.0636   0.02194   0.01812  -0.1356   0.7824   0.0043
  -4.250   0.1116   0.01878   0.01457  -0.1352   0.7793   0.0059
  -4.000   0.1354   0.01637   0.01189  -0.1345   0.7776   0.0060
  -3.750   0.1593   0.01384   0.00900  -0.1337   0.7759   0.0057
  -3.500   0.1839   0.01160   0.00642  -0.1328   0.7742   0.0053
  -3.250   0.2088   0.01002   0.00459  -0.1321   0.7726   0.0051
  -3.000   0.2336   0.00897   0.00337  -0.1314   0.7708   0.0050
  -2.750   0.2588   0.00832   0.00258  -0.1309   0.7691   0.0051
  -2.250   0.3110   0.00759   0.00168  -0.1304   0.7659   0.0074
  -2.000   0.3379   0.00750   0.00159  -0.1304   0.7640   0.0092
  -1.750   0.3643   0.00727   0.00129  -0.1302   0.7619   0.0114
  -1.500   0.3911   0.00712   0.00109  -0.1300   0.7599   0.0138
  -1.250   0.4179   0.00701   0.00100  -0.1299   0.7578   0.0229
  -1.000   0.4445   0.00690   0.00093  -0.1299   0.7559   0.0454
  -0.750   0.4711   0.00678   0.00089  -0.1298   0.7540   0.0812
  -0.500   0.4930   0.00606   0.00091  -0.1292   0.7519   0.3611
  -0.250   0.5172   0.00574   0.00091  -0.1288   0.7495   0.4885
   0.000   0.5386   0.00529   0.00093  -0.1277   0.7469   0.6673
   0.250   0.5568   0.00497   0.00106  -0.1255   0.7443   0.8434
   0.500   0.5815   0.00494   0.00108  -0.1249   0.7419   0.8728
   0.750   0.6064   0.00491   0.00111  -0.1242   0.7392   0.8960
   1.000   0.6316   0.00487   0.00115  -0.1237   0.7360   0.9159
   1.250   0.6581   0.00486   0.00116  -0.1235   0.7326   0.9282
   1.500   0.6855   0.00486   0.00117  -0.1236   0.7294   0.9358
   1.750   0.7137   0.00487   0.00121  -0.1238   0.7261   0.9441
   2.000   0.7444   0.00487   0.00125  -0.1247   0.7218   0.9535
   2.250   0.7773   0.00488   0.00131  -0.1261   0.7140   0.9634
   2.500   0.8110   0.00493   0.00132  -0.1276   0.6903   0.9740
   2.750   0.8427   0.00518   0.00138  -0.1288   0.6420   0.9932
   3.250   0.8646   0.00649   0.00195  -0.1221   0.4786   1.0000
   3.500   0.8610   0.00811   0.00268  -0.1162   0.2905   1.0000
   3.750   0.8539   0.01009   0.00359  -0.1099   0.0522   1.0000
   4.000   0.8727   0.01059   0.00393  -0.1083   0.0157   1.0000
   4.250   0.8948   0.01087   0.00421  -0.1074   0.0087   1.0000
   4.500   0.9157   0.01124   0.00461  -0.1062   0.0037   1.0000
   4.750   0.9371   0.01158   0.00498  -0.1052   0.0028   1.0000
   5.000   0.9573   0.01199   0.00546  -0.1038   0.0025   1.0000
   5.250   0.9746   0.01260   0.00617  -0.1018   0.0022   1.0000
   5.500   0.9909   0.01324   0.00691  -0.0997   0.0022   1.0000
   5.750   1.0028   0.01407   0.00785  -0.0967   0.0022   1.0000
   6.000   1.0138   0.01502   0.00892  -0.0936   0.0022   1.0000
   6.250   1.0250   0.01616   0.01016  -0.0906   0.0022   1.0000
   6.500   1.0378   0.01763   0.01174  -0.0879   0.0022   1.0000
   6.750   1.0597   0.01945   0.01368  -0.0869   0.0023   1.0000
   7.000   1.0975   0.02227   0.01669  -0.0886   0.0025   1.0000
   7.250   1.1305   0.02546   0.02018  -0.0892   0.0027   1.0000
   7.500   1.1549   0.02866   0.02367  -0.0883   0.0028   1.0000
   7.750   1.1746   0.03136   0.02660  -0.0866   0.0027   1.0000
   8.000   1.1925   0.03287   0.02827  -0.0852   0.0022   1.0000
   8.250   1.2060   0.03604   0.03171  -0.0826   0.0022   1.0000
   8.500   1.2164   0.03922   0.03516  -0.0796   0.0021   1.0000
   8.750   1.2267   0.04101   0.03711  -0.0774   0.0019   1.0000
   9.000   1.2296   0.04497   0.04135  -0.0735   0.0019   1.0000
   9.250   1.2357   0.04639   0.04290  -0.0710   0.0017   1.0000
   9.500   1.2333   0.05006   0.04681  -0.0669   0.0017   1.0000
   9.750   1.2308   0.05235   0.04927  -0.0633   0.0016   1.0000
  10.000   1.2255   0.05402   0.05106  -0.0595   0.0015   1.0000
  10.250   1.2158   0.05616   0.05334  -0.0554   0.0014   1.0000
  10.500   1.2014   0.05900   0.05634  -0.0513   0.0014   1.0000
  10.750   1.1852   0.06191   0.05939  -0.0478   0.0014   1.0000
  11.000   1.1678   0.06603   0.06368  -0.0446   0.0014   1.0000
  11.250   1.1489   0.06915   0.06693  -0.0426   0.0013   1.0000
  11.500   1.1300   0.07381   0.07173  -0.0407   0.0014   1.0000
  11.750   1.1084   0.07815   0.07620  -0.0400   0.0013   1.0000
  12.000   1.0878   0.08405   0.08223  -0.0397   0.0014   1.0000
  12.250   1.0679   0.08902   0.08730  -0.0408   0.0013   1.0000
  12.500   1.0428   0.09580   0.09419  -0.0434   0.0013   1.0000
  12.750   1.0234   0.10379   0.10229  -0.0467   0.0014   1.0000
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