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WORTMANN FX 71-089A AIRFOIL (fx71089a-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 71-089A AIRFOIL (fx71089a-il)
Reynolds number: 500,000
Max Cl/Cd: 46.11 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx71089a-il-500000.txt
Download as CSV file: xf-fx71089a-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 71-089A AIRFOIL                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.9332   0.06903   0.06601  -0.0288   1.0000   0.0425
 -12.750  -0.9764   0.05920   0.05601  -0.0362   1.0000   0.0422
 -12.500  -1.0141   0.05298   0.04957  -0.0389   1.0000   0.0421
 -12.250  -1.0448   0.04893   0.04530  -0.0375   1.0000   0.0422
 -12.000  -1.0684   0.04615   0.04227  -0.0337   1.0000   0.0423
 -11.750  -1.0778   0.04405   0.03988  -0.0309   1.0000   0.0426
 -11.500  -1.0924   0.03929   0.03476  -0.0283   1.0000   0.0431
 -11.250  -1.0828   0.03703   0.03243  -0.0271   1.0000   0.0437
 -11.000  -1.0636   0.03633   0.03177  -0.0263   1.0000   0.0443
 -10.750  -1.0419   0.03606   0.03155  -0.0256   1.0000   0.0449
 -10.500  -1.0243   0.03529   0.03074  -0.0245   1.0000   0.0456
 -10.250  -1.0106   0.03391   0.02921  -0.0231   1.0000   0.0465
 -10.000  -0.9982   0.03219   0.02726  -0.0215   1.0000   0.0472
  -9.750  -0.9845   0.03050   0.02532  -0.0199   1.0000   0.0478
  -9.500  -0.9686   0.02914   0.02372  -0.0184   1.0000   0.0483
  -9.250  -0.9511   0.02795   0.02232  -0.0169   1.0000   0.0487
  -9.000  -0.9329   0.02664   0.02083  -0.0156   1.0000   0.0488
  -8.750  -0.9145   0.02530   0.01928  -0.0142   1.0000   0.0491
  -8.500  -0.8956   0.02349   0.01730  -0.0130   1.0000   0.0492
  -8.250  -0.8753   0.02196   0.01564  -0.0119   1.0000   0.0494
  -8.000  -0.8540   0.02066   0.01424  -0.0109   1.0000   0.0496
  -7.750  -0.8323   0.01950   0.01301  -0.0098   1.0000   0.0498
  -7.500  -0.8101   0.01853   0.01198  -0.0088   1.0000   0.0501
  -7.250  -0.7877   0.01769   0.01110  -0.0078   1.0000   0.0504
  -7.000  -0.7651   0.01696   0.01035  -0.0067   1.0000   0.0507
  -6.750  -0.7425   0.01630   0.00966  -0.0056   1.0000   0.0511
  -6.500  -0.7198   0.01569   0.00903  -0.0045   1.0000   0.0515
  -6.250  -0.6972   0.01513   0.00845  -0.0034   1.0000   0.0519
  -6.000  -0.6746   0.01462   0.00793  -0.0023   1.0000   0.0524
  -5.750  -0.6520   0.01416   0.00746  -0.0011   1.0000   0.0531
  -5.500  -0.6296   0.01370   0.00698   0.0001   1.0000   0.0536
  -5.250  -0.6073   0.01325   0.00651   0.0013   1.0000   0.0541
  -5.000  -0.5852   0.01283   0.00608   0.0026   1.0000   0.0546
  -4.750  -0.5632   0.01243   0.00568   0.0039   1.0000   0.0551
  -4.500  -0.5412   0.01209   0.00532   0.0052   1.0000   0.0556
  -4.250  -0.5193   0.01178   0.00501   0.0066   1.0000   0.0561
  -4.000  -0.4989   0.01128   0.00451   0.0081   1.0000   0.0570
  -3.750  -0.4780   0.01090   0.00417   0.0096   1.0000   0.0581
  -3.500  -0.4566   0.01064   0.00393   0.0110   1.0000   0.0592
  -3.250  -0.4352   0.01042   0.00373   0.0123   1.0000   0.0605
  -3.000  -0.4136   0.01025   0.00357   0.0136   1.0000   0.0622
  -2.750  -0.3731   0.01006   0.00340   0.0111   0.9964   0.0642
  -2.500  -0.3326   0.00971   0.00312   0.0085   0.9922   0.0684
  -2.250  -0.2913   0.00943   0.00289   0.0059   0.9865   0.0748
  -2.000  -0.2498   0.00894   0.00266   0.0030   0.9818   0.1113
  -1.750  -0.2121   0.00837   0.00245   0.0010   0.9734   0.1818
  -1.500  -0.1716   0.00780   0.00224  -0.0016   0.9624   0.2658
  -1.250  -0.1339   0.00722   0.00206  -0.0035   0.9471   0.3604
  -1.000  -0.0996   0.00669   0.00193  -0.0047   0.9287   0.4654
  -0.750  -0.0692   0.00625   0.00181  -0.0048   0.8945   0.5654
  -0.500  -0.0447   0.00599   0.00173  -0.0036   0.8546   0.6444
  -0.250  -0.0222   0.00585   0.00171  -0.0018   0.8109   0.7090
   0.000   0.0000   0.00583   0.00169   0.0000   0.7621   0.7619
   0.250   0.0222   0.00585   0.00171   0.0018   0.7093   0.8108
   0.500   0.0447   0.00599   0.00173   0.0035   0.6449   0.8539
   0.750   0.0691   0.00625   0.00181   0.0048   0.5651   0.8943
   1.000   0.0995   0.00669   0.00193   0.0047   0.4659   0.9285
   1.250   0.1341   0.00723   0.00207   0.0035   0.3604   0.9474
   1.500   0.1715   0.00781   0.00224   0.0016   0.2641   0.9624
   1.750   0.2125   0.00838   0.00245  -0.0011   0.1819   0.9735
   2.000   0.2500   0.00892   0.00266  -0.0031   0.1145   0.9818
   2.250   0.2912   0.00943   0.00289  -0.0059   0.0748   0.9865
   2.500   0.3323   0.00971   0.00312  -0.0084   0.0684   0.9921
   2.750   0.3733   0.01006   0.00340  -0.0111   0.0642   0.9964
   3.000   0.4135   0.01024   0.00357  -0.0136   0.0621   1.0000
   3.250   0.4351   0.01042   0.00373  -0.0123   0.0604   1.0000
   3.500   0.4565   0.01064   0.00393  -0.0109   0.0592   1.0000
   3.750   0.4779   0.01091   0.00417  -0.0096   0.0580   1.0000
   4.000   0.4988   0.01128   0.00452  -0.0081   0.0569   1.0000
   4.250   0.5192   0.01178   0.00500  -0.0066   0.0560   1.0000
   4.500   0.5412   0.01208   0.00532  -0.0052   0.0556   1.0000
   4.750   0.5631   0.01243   0.00567  -0.0039   0.0551   1.0000
   5.000   0.5851   0.01282   0.00607  -0.0026   0.0546   1.0000
   5.250   0.6073   0.01324   0.00651  -0.0013   0.0541   1.0000
   5.500   0.6295   0.01370   0.00698  -0.0001   0.0536   1.0000
   5.750   0.6519   0.01417   0.00746   0.0011   0.0531   1.0000
   6.000   0.6745   0.01463   0.00793   0.0023   0.0524   1.0000
   6.250   0.6972   0.01512   0.00844   0.0034   0.0519   1.0000
   6.500   0.7198   0.01569   0.00903   0.0046   0.0515   1.0000
   6.750   0.7424   0.01630   0.00965   0.0056   0.0511   1.0000
   7.000   0.7651   0.01696   0.01035   0.0067   0.0507   1.0000
   7.250   0.7876   0.01770   0.01111   0.0078   0.0504   1.0000
   7.500   0.8101   0.01853   0.01198   0.0088   0.0501   1.0000
   7.750   0.8322   0.01952   0.01302   0.0098   0.0498   1.0000
   8.000   0.8540   0.02067   0.01424   0.0109   0.0496   1.0000
   8.250   0.8752   0.02199   0.01567   0.0119   0.0494   1.0000
   8.500   0.8956   0.02348   0.01729   0.0130   0.0492   1.0000
   8.750   0.9146   0.02529   0.01927   0.0142   0.0491   1.0000
   9.000   0.9330   0.02655   0.02073   0.0156   0.0488   1.0000
   9.250   0.9513   0.02787   0.02224   0.0169   0.0487   1.0000
   9.500   0.9689   0.02900   0.02358   0.0183   0.0482   1.0000
   9.750   0.9849   0.03038   0.02519   0.0199   0.0477   1.0000
  10.000   0.9985   0.03213   0.02720   0.0215   0.0471   1.0000
  10.250   1.0111   0.03385   0.02914   0.0231   0.0464   1.0000
  10.500   1.0256   0.03511   0.03053   0.0244   0.0456   1.0000
  10.750   1.0432   0.03591   0.03138   0.0255   0.0448   1.0000
  11.000   1.0629   0.03646   0.03191   0.0263   0.0443   1.0000
  11.250   1.0828   0.03707   0.03247   0.0271   0.0437   1.0000
  11.500   1.0930   0.03921   0.03468   0.0283   0.0431   1.0000
  12.000   1.0683   0.04597   0.04211   0.0337   0.0422   1.0000
  12.250   1.0447   0.04896   0.04533   0.0374   0.0421   1.0000
  12.500   1.0141   0.05297   0.04956   0.0388   0.0420   1.0000
  12.750   0.9784   0.05917   0.05597   0.0362   0.0422   1.0000
  13.000   0.9414   0.06796   0.06490   0.0303   0.0426   1.0000
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