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WORTMANN FX 76-100 (fx76100-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 76-100 (fx76100-il)
Reynolds number: 100,000
Max Cl/Cd: 35.37 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx76100-il-100000.txt
Download as CSV file: xf-fx76100-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 76-100                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.8152   0.07073   0.06523  -0.0347   1.0000   0.0727
 -10.500  -0.8289   0.06607   0.06052  -0.0341   1.0000   0.0720
 -10.250  -0.8484   0.06181   0.05612  -0.0323   1.0000   0.0714
 -10.000  -0.8633   0.05743   0.05153  -0.0304   1.0000   0.0707
  -9.750  -0.8753   0.05307   0.04688  -0.0282   1.0000   0.0701
  -9.500  -0.8842   0.04883   0.04225  -0.0256   1.0000   0.0700
  -9.250  -0.8876   0.04498   0.03796  -0.0229   1.0000   0.0704
  -9.000  -0.8862   0.04186   0.03432  -0.0200   1.0000   0.0718
  -8.750  -0.8819   0.03924   0.03114  -0.0170   1.0000   0.0733
  -8.500  -0.8682   0.03587   0.02767  -0.0157   1.0000   0.0761
  -8.250  -0.8524   0.03367   0.02526  -0.0140   1.0000   0.0785
  -8.000  -0.8365   0.03184   0.02315  -0.0121   1.0000   0.0828
  -7.750  -0.8206   0.02984   0.02072  -0.0100   1.0000   0.0869
  -7.500  -0.7998   0.02791   0.01885  -0.0090   1.0000   0.0915
  -7.250  -0.7805   0.02659   0.01726  -0.0073   1.0000   0.0980
  -7.000  -0.7598   0.02496   0.01568  -0.0061   1.0000   0.1050
  -6.750  -0.7391   0.02371   0.01420  -0.0046   1.0000   0.1135
  -6.500  -0.7191   0.02252   0.01311  -0.0032   1.0000   0.1252
  -6.250  -0.6995   0.02137   0.01202  -0.0016   1.0000   0.1395
  -6.000  -0.6810   0.02031   0.01106   0.0001   1.0000   0.1587
  -5.750  -0.6631   0.01942   0.01025   0.0020   1.0000   0.1859
  -5.500  -0.6461   0.01856   0.00959   0.0039   1.0000   0.2181
  -5.250  -0.6290   0.01787   0.00907   0.0059   1.0000   0.2521
  -5.000  -0.6112   0.01729   0.00860   0.0078   1.0000   0.2850
  -4.750  -0.5929   0.01676   0.00815   0.0096   1.0000   0.3160
  -4.500  -0.5743   0.01625   0.00776   0.0114   1.0000   0.3468
  -4.250  -0.5555   0.01576   0.00739   0.0131   1.0000   0.3784
  -4.000  -0.5368   0.01528   0.00705   0.0150   1.0000   0.4134
  -3.750  -0.5184   0.01478   0.00674   0.0169   1.0000   0.4515
  -3.500  -0.5003   0.01429   0.00648   0.0189   1.0000   0.4955
  -3.250  -0.4825   0.01381   0.00629   0.0211   1.0000   0.5458
  -3.000  -0.4648   0.01338   0.00616   0.0235   1.0000   0.6052
  -2.750  -0.4462   0.01303   0.00613   0.0260   1.0000   0.6707
  -2.500  -0.4252   0.01285   0.00622   0.0283   1.0000   0.7396
  -2.250  -0.3999   0.01289   0.00642   0.0301   1.0000   0.8059
  -2.000  -0.3648   0.01314   0.00671   0.0300   1.0000   0.8617
  -1.750  -0.3159   0.01354   0.00706   0.0271   1.0000   0.9056
  -1.500  -0.2527   0.01400   0.00737   0.0211   1.0000   0.9358
  -1.250  -0.1816   0.01435   0.00758   0.0132   1.0000   0.9574
  -1.000  -0.1068   0.01448   0.00758   0.0042   1.0000   0.9748
  -0.750  -0.0333   0.01437   0.00739  -0.0050   1.0000   0.9915
  -0.500   0.0081   0.01414   0.00713  -0.0089   1.0000   1.0000
  -0.250   0.0050   0.01400   0.00700  -0.0046   1.0000   1.0000
   0.000   0.0000   0.01396   0.00696   0.0000   1.0000   1.0000
   0.250  -0.0050   0.01400   0.00700   0.0046   1.0000   1.0000
   0.500  -0.0081   0.01414   0.00713   0.0089   1.0000   1.0000
   0.750   0.0330   0.01437   0.00739   0.0051   0.9916   1.0000
   1.000   0.1070   0.01447   0.00758  -0.0042   0.9747   1.0000
   1.250   0.1815   0.01435   0.00758  -0.0132   0.9576   1.0000
   1.500   0.2531   0.01400   0.00738  -0.0211   0.9357   1.0000
   1.750   0.3161   0.01354   0.00705  -0.0271   0.9053   1.0000
   2.000   0.3648   0.01314   0.00671  -0.0300   0.8618   1.0000
   2.250   0.3999   0.01289   0.00642  -0.0301   0.8058   1.0000
   2.500   0.4252   0.01285   0.00622  -0.0283   0.7398   1.0000
   2.750   0.4461   0.01303   0.00613  -0.0260   0.6707   1.0000
   3.000   0.4647   0.01338   0.00616  -0.0235   0.6052   1.0000
   3.250   0.4824   0.01381   0.00629  -0.0211   0.5458   1.0000
   3.500   0.5002   0.01429   0.00648  -0.0189   0.4954   1.0000
   3.750   0.5184   0.01478   0.00674  -0.0169   0.4514   1.0000
   4.000   0.5368   0.01529   0.00704  -0.0149   0.4136   1.0000
   4.250   0.5554   0.01576   0.00739  -0.0131   0.3785   1.0000
   4.500   0.5742   0.01625   0.00776  -0.0113   0.3465   1.0000
   4.750   0.5928   0.01676   0.00815  -0.0096   0.3158   1.0000
   5.000   0.6111   0.01729   0.00859  -0.0078   0.2847   1.0000
   5.250   0.6289   0.01786   0.00906  -0.0059   0.2520   1.0000
   5.500   0.6461   0.01855   0.00959  -0.0039   0.2181   1.0000
   5.750   0.6630   0.01941   0.01024  -0.0020   0.1858   1.0000
   6.000   0.6808   0.02032   0.01106  -0.0001   0.1584   1.0000
   6.250   0.6994   0.02138   0.01203   0.0016   0.1391   1.0000
   6.500   0.7191   0.02254   0.01313   0.0032   0.1250   1.0000
   6.750   0.7391   0.02373   0.01422   0.0046   0.1135   1.0000
   7.000   0.7597   0.02496   0.01568   0.0062   0.1049   1.0000
   7.250   0.7804   0.02658   0.01726   0.0074   0.0979   1.0000
   7.500   0.7998   0.02792   0.01885   0.0090   0.0915   1.0000
   7.750   0.8206   0.02984   0.02072   0.0101   0.0869   1.0000
   8.000   0.8366   0.03189   0.02319   0.0121   0.0831   1.0000
   8.250   0.8523   0.03370   0.02531   0.0140   0.0788   1.0000
   8.500   0.8682   0.03589   0.02770   0.0157   0.0761   1.0000
   8.750   0.8824   0.03892   0.03084   0.0171   0.0737   1.0000
   9.000   0.8870   0.04199   0.03442   0.0199   0.0721   1.0000
   9.250   0.8881   0.04508   0.03804   0.0228   0.0707   1.0000
   9.500   0.8844   0.04888   0.04231   0.0256   0.0701   1.0000
   9.750   0.8766   0.05304   0.04684   0.0281   0.0703   1.0000
  10.000   0.8641   0.05744   0.05154   0.0304   0.0708   1.0000
  10.250   0.8480   0.06189   0.05621   0.0322   0.0714   1.0000
  10.500   0.8301   0.06608   0.06052   0.0340   0.0720   1.0000
  10.750   0.8120   0.07076   0.06528   0.0346   0.0726   1.0000
  11.000   0.8013   0.07614   0.07069   0.0341   0.0732   1.0000
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