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WORTMANN FX 74-080 (fx74080-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 74-080 (fx74080-il)
Reynolds number: 500,000
Max Cl/Cd: 134.44 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx74080-il-500000.txt
Download as CSV file: xf-fx74080-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.1192   0.08704   0.08462  -0.0859   0.9261   0.0075
 -10.000  -0.1103   0.08317   0.08072  -0.0883   0.9216   0.0078
  -9.750  -0.1023   0.07951   0.07704  -0.0905   0.9168   0.0081
  -9.500  -0.0938   0.07582   0.07331  -0.0928   0.9126   0.0084
  -9.250  -0.0861   0.07215   0.06961  -0.0949   0.9088   0.0085
  -9.000  -0.0799   0.06862   0.06607  -0.0966   0.9043   0.0089
  -8.750  -0.0726   0.06510   0.06253  -0.0986   0.9003   0.0091
  -8.500  -0.0649   0.06137   0.05877  -0.1010   0.8971   0.0096
  -8.250  -0.0596   0.05801   0.05541  -0.1025   0.8933   0.0101
  -8.000  -0.0538   0.05463   0.05203  -0.1045   0.8895   0.0109
  -7.750  -0.0471   0.05132   0.04870  -0.1067   0.8859   0.0113
  -5.250   0.0397   0.03355   0.02997  -0.1406   0.8590   0.0139
  -5.000   0.0585   0.03100   0.02727  -0.1409   0.8564   0.0145
  -4.750   0.0765   0.02994   0.02617  -0.1409   0.8535   0.0181
  -4.500   0.0990   0.02756   0.02357  -0.1406   0.8507   0.0204
  -4.250   0.1283   0.02693   0.02267  -0.1399   0.8483   0.0232
  -4.000   0.1526   0.02513   0.02055  -0.1396   0.8460   0.0234
  -3.000   0.2432   0.01464   0.00887  -0.1369   0.8363   0.0186
  -2.750   0.2697   0.01244   0.00628  -0.1358   0.8341   0.0142
  -2.500   0.2954   0.01128   0.00498  -0.1352   0.8321   0.0152
  -2.250   0.3214   0.01072   0.00434  -0.1349   0.8301   0.0176
  -2.000   0.3460   0.01046   0.00404  -0.1344   0.8275   0.0218
  -1.750   0.3705   0.00998   0.00349  -0.1337   0.8248   0.0228
  -1.500   0.3954   0.00940   0.00286  -0.1330   0.8222   0.0488
  -1.250   0.4176   0.00853   0.00279  -0.1326   0.8199   0.3263
  -1.000   0.4277   0.00735   0.00303  -0.1290   0.8176   0.8213
  -0.750   0.4448   0.00726   0.00311  -0.1262   0.8146   0.9038
  -0.500   0.4687   0.00721   0.00308  -0.1252   0.8117   0.9332
  -0.250   0.5193   0.00711   0.00294  -0.1302   0.8099   0.9782
   0.000   0.5832   0.00708   0.00283  -0.1383   0.8086   1.0000
   0.250   0.6060   0.00713   0.00283  -0.1375   0.8060   1.0000
   0.500   0.6295   0.00722   0.00288  -0.1369   0.8036   1.0000
   0.750   0.6490   0.00728   0.00297  -0.1354   0.7998   1.0000
   1.000   0.6723   0.00733   0.00302  -0.1347   0.7964   1.0000
   1.250   0.6979   0.00738   0.00305  -0.1344   0.7936   1.0000
   1.500   0.7254   0.00746   0.00310  -0.1345   0.7912   1.0000
   1.750   0.7486   0.00753   0.00321  -0.1338   0.7873   1.0000
   2.000   0.7737   0.00758   0.00329  -0.1333   0.7834   1.0000
   2.250   0.8005   0.00762   0.00339  -0.1333   0.7803   1.0000
   2.500   0.8290   0.00769   0.00347  -0.1336   0.7776   1.0000
   2.750   0.8518   0.00771   0.00358  -0.1326   0.7719   1.0000
   3.000   0.8757   0.00736   0.00322  -0.1314   0.7575   1.0000
   3.250   0.8980   0.00705   0.00290  -0.1298   0.7396   1.0000
   3.500   0.9142   0.00680   0.00258  -0.1269   0.6976   1.0000
   3.750   0.9111   0.00760   0.00268  -0.1199   0.5525   1.0000
   4.000   0.8888   0.01001   0.00373  -0.1105   0.2874   1.0000
   4.250   0.8719   0.01261   0.00504  -0.1025   0.0239   1.0000
   4.500   0.8849   0.01350   0.00608  -0.0995   0.0153   1.0000
   4.750   0.8985   0.01428   0.00697  -0.0968   0.0142   1.0000
   5.000   0.9167   0.01469   0.00739  -0.0951   0.0118   1.0000
   5.250   0.9281   0.01550   0.00829  -0.0920   0.0104   1.0000
   5.500   0.9386   0.01646   0.00931  -0.0888   0.0093   1.0000
   5.750   0.9478   0.01770   0.01063  -0.0854   0.0086   1.0000
   6.000   0.9628   0.01905   0.01207  -0.0831   0.0093   1.0000
   7.000   1.1139   0.03781   0.03186  -0.0887   0.0146   1.0000
   7.250   1.1280   0.04051   0.03483  -0.0862   0.0146   1.0000
   7.500   1.1395   0.04303   0.03764  -0.0834   0.0145   1.0000
   7.750   1.1495   0.04534   0.04022  -0.0805   0.0144   1.0000
   8.000   1.1671   0.04442   0.03951  -0.0778   0.0133   1.0000
   8.250   1.1844   0.04524   0.04054  -0.0755   0.0109   1.0000
   8.500   1.1911   0.04765   0.04317  -0.0726   0.0097   1.0000
   8.750   1.1944   0.05020   0.04592  -0.0695   0.0091   1.0000
   9.000   1.1945   0.05287   0.04878  -0.0662   0.0086   1.0000
   9.250   1.1917   0.05538   0.05142  -0.0630   0.0082   1.0000
   9.500   1.1863   0.05826   0.05448  -0.0593   0.0080   1.0000
   9.750   1.1730   0.06095   0.05730  -0.0548   0.0077   1.0000
  10.000   1.1598   0.06363   0.06014  -0.0504   0.0077   1.0000
  10.250   1.1409   0.06685   0.06351  -0.0465   0.0075   1.0000
  10.500   1.1138   0.07136   0.06817  -0.0430   0.0073   1.0000
  10.750   1.0989   0.07454   0.07150  -0.0407   0.0073   1.0000
  11.000   1.0817   0.07823   0.07533  -0.0390   0.0073   1.0000
  11.250   1.0614   0.08269   0.07992  -0.0380   0.0073   1.0000
  11.500   1.0484   0.08640   0.08376  -0.0377   0.0074   1.0000
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