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FX 77-W-121 (fx77w121-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 77-W-121 (fx77w121-il)
Reynolds number: 200,000
Max Cl/Cd: 71.88 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx77w121-il-200000.txt
Download as CSV file: xf-fx77w121-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 77-W-121                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2078   0.09238   0.08802  -0.0213   0.5877   0.0362
  -9.250  -0.2034   0.08914   0.08474  -0.0222   0.5852   0.0370
  -9.000  -0.2003   0.08580   0.08137  -0.0232   0.5830   0.0378
  -8.750  -0.1978   0.08235   0.07795  -0.0243   0.5801   0.0388
  -8.500  -0.1963   0.07885   0.07446  -0.0256   0.5779   0.0398
  -8.250  -0.1961   0.07531   0.07092  -0.0269   0.5756   0.0409
  -8.000  -0.1983   0.07187   0.06750  -0.0288   0.5739   0.0423
  -7.750  -0.2056   0.06851   0.06416  -0.0318   0.5726   0.0434
  -7.500  -0.2112   0.06517   0.06083  -0.0344   0.5712   0.0437
  -7.250  -0.2279   0.06206   0.05772  -0.0381   0.5702   0.0441
  -7.000  -0.2321   0.05833   0.05393  -0.0401   0.5689   0.0443
  -6.750  -0.2324   0.05443   0.04994  -0.0415   0.5673   0.0444
  -6.250  -0.2556   0.05993   0.05494  -0.0463   0.5669   0.0458
  -6.000  -0.2431   0.05765   0.05271  -0.0454   0.5643   0.0472
  -5.750  -0.2308   0.05490   0.04989  -0.0453   0.5621   0.0483
  -5.500  -0.2170   0.05245   0.04733  -0.0452   0.5599   0.0530
  -5.250  -0.1996   0.05156   0.04572  -0.0448   0.5581   0.0576
  -5.000  -0.1919   0.04517   0.03939  -0.0447   0.5563   0.0595
  -4.750  -0.1750   0.04297   0.03715  -0.0441   0.5543   0.0615
  -4.500  -0.1572   0.04089   0.03496  -0.0433   0.5525   0.0649
  -4.250  -0.1414   0.03841   0.03193  -0.0416   0.5508   0.0733
  -4.000  -0.1191   0.01518   0.00951  -0.0385   0.5477   0.0767
  -3.750  -0.1023   0.01317   0.00707  -0.0370   0.5460   0.0878
  -3.500  -0.0830   0.01140   0.00533  -0.0365   0.5441   0.0915
  -3.250  -0.0598   0.02733   0.01951  -0.0350   0.5440   0.0603
  -3.000  -0.0349   0.02445   0.01620  -0.0333   0.5424   0.0500
  -2.750  -0.0087   0.02228   0.01348  -0.0318   0.5407   0.0475
  -2.500   0.0179   0.02117   0.01213  -0.0311   0.5389   0.0487
  -2.250   0.0444   0.02055   0.01144  -0.0307   0.5372   0.0531
  -2.000   0.0718   0.01977   0.01052  -0.0302   0.5354   0.0559
  -1.750   0.0989   0.01895   0.00962  -0.0298   0.5338   0.0588
  -1.500   0.1244   0.01831   0.00906  -0.0293   0.5321   0.0654
  -1.250   0.1501   0.01793   0.00863  -0.0287   0.5304   0.0706
  -1.000   0.1741   0.01744   0.00818  -0.0278   0.5286   0.0799
  -0.750   0.3471   0.01418   0.00752  -0.0579   0.5250   1.0000
  -0.500   0.3718   0.01444   0.00760  -0.0574   0.5237   1.0000
  -0.250   0.3964   0.01464   0.00774  -0.0569   0.5222   1.0000
   0.000   0.4209   0.01487   0.00791  -0.0564   0.5204   1.0000
   0.250   0.4455   0.01512   0.00811  -0.0559   0.5187   1.0000
   0.500   0.4701   0.01537   0.00829  -0.0555   0.5168   1.0000
   0.750   0.4948   0.01559   0.00843  -0.0549   0.5147   1.0000
   1.000   0.5195   0.01582   0.00859  -0.0545   0.5129   1.0000
   1.250   0.5444   0.01609   0.00879  -0.0540   0.5115   1.0000
   1.500   0.5692   0.01638   0.00900  -0.0535   0.5099   1.0000
   1.750   0.5936   0.01677   0.00934  -0.0530   0.5082   1.0000
   2.000   0.6170   0.01714   0.00979  -0.0525   0.5055   1.0000
   2.250   0.6409   0.01751   0.01017  -0.0521   0.5029   1.0000
   2.500   0.6651   0.01785   0.01051  -0.0516   0.5006   1.0000
   2.750   0.6895   0.01817   0.01083  -0.0511   0.4988   1.0000
   3.000   0.7144   0.01842   0.01103  -0.0506   0.4968   1.0000
   3.250   0.7393   0.01872   0.01128  -0.0501   0.4951   1.0000
   3.500   0.7628   0.01922   0.01180  -0.0496   0.4930   1.0000
   3.750   0.7842   0.01985   0.01258  -0.0491   0.4898   1.0000
   4.000   0.8071   0.02029   0.01309  -0.0485   0.4866   1.0000
   4.250   0.8317   0.02051   0.01330  -0.0480   0.4838   1.0000
   4.500   0.8572   0.02065   0.01339  -0.0475   0.4816   1.0000
   4.750   0.8828   0.02085   0.01355  -0.0470   0.4796   1.0000
   5.000   0.9018   0.02167   0.01457  -0.0462   0.4753   1.0000
   5.250   0.9235   0.02220   0.01520  -0.0456   0.4717   1.0000
   5.500   0.9482   0.02236   0.01536  -0.0450   0.4688   1.0000
   5.750   0.9746   0.02237   0.01537  -0.0446   0.4665   1.0000
   6.000   1.0011   0.02248   0.01543  -0.0442   0.4644   1.0000
   6.250   1.0164   0.02346   0.01668  -0.0430   0.4583   1.0000
   6.500   1.0405   0.02360   0.01687  -0.0425   0.4548   1.0000
   6.750   1.0672   0.02355   0.01684  -0.0420   0.4523   1.0000
   7.000   1.0941   0.02358   0.01686  -0.0417   0.4502   1.0000
   7.250   1.1082   0.02469   0.01822  -0.0404   0.4444   1.0000
   7.500   1.1312   0.02491   0.01854  -0.0398   0.4405   1.0000
   7.750   1.1584   0.02475   0.01842  -0.0394   0.4377   1.0000
   8.000   1.1874   0.02451   0.01817  -0.0392   0.4354   1.0000
   8.250   1.1994   0.02560   0.01954  -0.0376   0.4286   1.0000
   8.500   1.2247   0.02551   0.01954  -0.0371   0.4247   1.0000
   8.750   1.2537   0.02513   0.01920  -0.0368   0.4219   1.0000
   9.000   1.2731   0.02541   0.01965  -0.0357   0.4161   1.0000
   9.250   1.3053   0.02378   0.01801  -0.0353   0.4083   1.0000
   9.500   1.3311   0.02245   0.01676  -0.0342   0.3975   1.0000
   9.750   1.3573   0.02114   0.01552  -0.0332   0.3861   1.0000
  10.000   1.3788   0.02026   0.01482  -0.0318   0.3697   1.0000
  10.250   1.3995   0.01947   0.01403  -0.0303   0.3406   1.0000
  10.500   1.4072   0.01982   0.01407  -0.0274   0.2898   1.0000
  10.750   1.3937   0.02183   0.01568  -0.0227   0.2371   1.0000
  11.000   1.3702   0.02429   0.01793  -0.0174   0.2006   1.0000
  11.250   1.3459   0.02771   0.02127  -0.0148   0.1763   1.0000
  11.500   1.3242   0.03231   0.02581  -0.0148   0.1525   1.0000
  11.750   1.2986   0.03765   0.03100  -0.0152   0.1261   1.0000
  12.000   1.2664   0.04367   0.03680  -0.0155   0.0954   1.0000
  12.250   1.2511   0.04789   0.04096  -0.0155   0.0790   1.0000
  12.500   1.2331   0.05241   0.04537  -0.0156   0.0604   1.0000
  12.750   1.2089   0.05768   0.05047  -0.0158   0.0432   1.0000
  13.000   1.1909   0.06260   0.05533  -0.0161   0.0340   1.0000
  13.250   1.1830   0.06655   0.05938  -0.0164   0.0304   1.0000
  13.500   1.1751   0.07058   0.06347  -0.0169   0.0281   1.0000
  13.750   1.1652   0.07500   0.06796  -0.0175   0.0264   1.0000
  14.000   1.1567   0.07931   0.07238  -0.0181   0.0245   1.0000
  14.250   1.1532   0.08297   0.07614  -0.0186   0.0239   1.0000
  14.500   1.1502   0.08660   0.07984  -0.0191   0.0219   1.0000
  14.750   1.1486   0.08995   0.08329  -0.0195   0.0221   1.0000
  15.000   1.1474   0.09317   0.08654  -0.0196   0.0211   1.0000
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