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FX 77-W-121 (fx77w121-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 77-W-121 (fx77w121-il)
Reynolds number: 100,000
Max Cl/Cd: 37.46 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx77w121-il-100000-n5.txt
Download as CSV file: xf-fx77w121-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3140   0.11286   0.10719  -0.0208   0.6106   0.0439
  -9.500  -0.3141   0.11009   0.10444  -0.0241   0.6053   0.0442
  -9.250  -0.3127   0.10717   0.10151  -0.0270   0.6006   0.0444
  -9.000  -0.3087   0.10363   0.09797  -0.0291   0.5962   0.0444
  -8.750  -0.2895   0.09800   0.09229  -0.0257   0.5900   0.0465
  -8.500  -0.2788   0.09502   0.08927  -0.0257   0.5856   0.0486
  -8.250  -0.2744   0.09186   0.08609  -0.0271   0.5823   0.0497
  -8.000  -0.2710   0.08882   0.08309  -0.0286   0.5786   0.0510
  -7.750  -0.2703   0.08555   0.07984  -0.0304   0.5755   0.0520
  -7.500  -0.2706   0.08238   0.07668  -0.0322   0.5727   0.0524
  -7.250  -0.2745   0.07925   0.07355  -0.0338   0.5704   0.0534
  -7.000  -0.2727   0.07580   0.07006  -0.0358   0.5680   0.0534
  -6.750  -0.2680   0.07230   0.06655  -0.0378   0.5651   0.0532
  -6.500  -0.2680   0.06357   0.05755  -0.0431   0.5640   0.0325
  -6.250  -0.2600   0.06006   0.05397  -0.0432   0.5613   0.0316
  -6.000  -0.2503   0.05656   0.05033  -0.0436   0.5588   0.0307
  -5.750  -0.2397   0.05281   0.04637  -0.0438   0.5564   0.0299
  -5.500  -0.2281   0.04888   0.04217  -0.0436   0.5544   0.0294
  -5.250  -0.2150   0.04512   0.03810  -0.0430   0.5520   0.0289
  -5.000  -0.2001   0.04171   0.03434  -0.0421   0.5492   0.0291
  -4.750  -0.1835   0.03872   0.03096  -0.0409   0.5466   0.0304
  -4.500  -0.1658   0.03587   0.02761  -0.0394   0.5443   0.0316
  -4.250  -0.1469   0.03325   0.02448  -0.0378   0.5421   0.0321
  -4.000  -0.1262   0.03094   0.02162  -0.0362   0.5402   0.0326
  -3.750  -0.1037   0.02911   0.01929  -0.0349   0.5385   0.0331
  -3.500  -0.0810   0.02722   0.01717  -0.0341   0.5362   0.0348
  -3.250  -0.0567   0.02631   0.01614  -0.0336   0.5337   0.0380
  -3.000  -0.0308   0.02512   0.01464  -0.0329   0.5312   0.0404
  -2.750  -0.0038   0.02393   0.01316  -0.0323   0.5289   0.0424
  -2.500   0.0228   0.02299   0.01201  -0.0318   0.5267   0.0457
  -2.250   0.0486   0.02225   0.01123  -0.0314   0.5250   0.0501
  -2.000   0.0747   0.02158   0.01042  -0.0308   0.5234   0.0536
  -1.750   0.0997   0.02106   0.00986  -0.0302   0.5214   0.0592
  -1.500   0.1243   0.02066   0.00947  -0.0296   0.5194   0.0664
  -1.250   0.1492   0.02028   0.00903  -0.0289   0.5172   0.0741
  -1.000   0.1748   0.01995   0.00871  -0.0284   0.5150   0.0923
  -0.750   0.3331   0.01696   0.00820  -0.0550   0.5115   1.0000
  -0.500   0.3577   0.01714   0.00813  -0.0544   0.5100   1.0000
  -0.250   0.3825   0.01734   0.00812  -0.0539   0.5087   1.0000
   0.000   0.4069   0.01760   0.00827  -0.0534   0.5068   1.0000
   0.250   0.4313   0.01786   0.00845  -0.0529   0.5047   1.0000
   0.500   0.4557   0.01812   0.00861  -0.0524   0.5023   1.0000
   0.750   0.4801   0.01837   0.00876  -0.0519   0.5003   1.0000
   1.000   0.5046   0.01864   0.00893  -0.0514   0.4985   1.0000
   1.250   0.5291   0.01891   0.00910  -0.0509   0.4969   1.0000
   1.500   0.5538   0.01919   0.00928  -0.0504   0.4955   1.0000
   1.750   0.5785   0.01947   0.00946  -0.0499   0.4941   1.0000
   2.000   0.6019   0.01990   0.00991  -0.0495   0.4917   1.0000
   2.250   0.6253   0.02032   0.01037  -0.0490   0.4891   1.0000
   2.500   0.6489   0.02074   0.01079  -0.0485   0.4869   1.0000
   2.750   0.6727   0.02111   0.01115  -0.0480   0.4847   1.0000
   3.000   0.6968   0.02144   0.01146  -0.0475   0.4827   1.0000
   3.250   0.7212   0.02172   0.01169  -0.0469   0.4808   1.0000
   3.500   0.7460   0.02200   0.01191  -0.0464   0.4791   1.0000
   3.750   0.7669   0.02269   0.01274  -0.0459   0.4758   1.0000
   4.000   0.7888   0.02328   0.01343  -0.0453   0.4728   1.0000
   4.250   0.8115   0.02374   0.01393  -0.0447   0.4701   1.0000
   4.500   0.8350   0.02411   0.01432  -0.0441   0.4679   1.0000
   4.750   0.8593   0.02439   0.01459  -0.0436   0.4658   1.0000
   5.000   0.8836   0.02471   0.01493  -0.0430   0.4639   1.0000
   5.250   0.9004   0.02572   0.01616  -0.0422   0.4591   1.0000
   5.500   0.9218   0.02623   0.01676  -0.0415   0.4555   1.0000
   6.000   0.9707   0.02661   0.01720  -0.0403   0.4505   1.0000
   6.250   0.9879   0.02753   0.01830  -0.0394   0.4462   1.0000
   6.500   1.0054   0.02834   0.01927  -0.0385   0.4416   1.0000
   6.750   1.0283   0.02862   0.01962  -0.0377   0.4385   1.0000
   7.000   1.0539   0.02865   0.01972  -0.0372   0.4361   1.0000
   7.250   1.0680   0.02970   0.02096  -0.0360   0.4309   1.0000
   7.500   1.0842   0.03047   0.02190  -0.0349   0.4257   1.0000
   7.750   1.1087   0.03051   0.02202  -0.0342   0.4227   1.0000
   8.000   1.1363   0.03033   0.02193  -0.0337   0.4205   1.0000
   8.250   1.1351   0.03249   0.02440  -0.0316   0.4123   1.0000
   8.500   1.1564   0.03274   0.02477  -0.0308   0.4087   1.0000
   8.750   1.1842   0.03245   0.02458  -0.0302   0.4062   1.0000
   9.000   1.1737   0.03510   0.02751  -0.0276   0.3971   1.0000
   9.250   1.1966   0.03506   0.02759  -0.0266   0.3934   1.0000
   9.500   1.2108   0.03567   0.02840  -0.0253   0.3888   1.0000
   9.750   1.1248   0.04425   0.03699  -0.0212   0.3714   1.0000
  10.250   1.1113   0.05049   0.04338  -0.0209   0.3530   1.0000
  10.500   1.1385   0.04957   0.04265  -0.0197   0.3510   1.0000
  11.000   1.1494   0.05306   0.04637  -0.0188   0.3368   1.0000
  11.500   1.1504   0.05784   0.05135  -0.0183   0.3195   1.0000
  11.750   1.1689   0.05761   0.05127  -0.0175   0.3098   1.0000
  12.000   1.1897   0.05675   0.05050  -0.0167   0.2921   1.0000
  12.250   1.1942   0.05825   0.05197  -0.0163   0.2716   1.0000
  12.500   1.2000   0.05950   0.05310  -0.0157   0.2464   1.0000
  12.750   1.1977   0.06187   0.05530  -0.0153   0.2204   1.0000
  13.000   1.1883   0.06531   0.05859  -0.0153   0.1953   1.0000
  13.250   1.1770   0.06932   0.06246  -0.0156   0.1694   1.0000
  13.500   1.1644   0.07369   0.06664  -0.0162   0.1392   1.0000
  13.750   1.1495   0.07855   0.07127  -0.0170   0.1098   1.0000
  14.000   1.1314   0.08405   0.07653  -0.0181   0.0824   1.0000
  14.250   1.1155   0.08944   0.08173  -0.0192   0.0601   1.0000
  14.500   1.1029   0.09456   0.08676  -0.0203   0.0476   1.0000
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