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FX 77-W-121 (fx77w121-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 77-W-121 (fx77w121-il)
Reynolds number: 500,000
Max Cl/Cd: 115.46 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx77w121-il-500000.txt
Download as CSV file: xf-fx77w121-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2750   0.09274   0.08877  -0.0326   0.5129   0.0178
  -8.750  -0.2713   0.08936   0.08538  -0.0338   0.5108   0.0178
  -8.500  -0.2699   0.08594   0.08196  -0.0360   0.5095   0.0178
  -8.250  -0.2691   0.08239   0.07843  -0.0379   0.5076   0.0179
  -8.000  -0.2709   0.07876   0.07485  -0.0398   0.5061   0.0178
  -7.750  -0.2866   0.07365   0.06979  -0.0403   0.5052   0.0184
  -7.500  -0.2893   0.07006   0.06619  -0.0420   0.5039   0.0183
  -7.250  -0.2821   0.06847   0.06460  -0.0408   0.5021   0.0191
  -7.000  -0.2793   0.06488   0.06098  -0.0424   0.5007   0.0192
  -6.750  -0.2735   0.06160   0.05765  -0.0436   0.4991   0.0194
  -6.500  -0.2663   0.05833   0.05431  -0.0444   0.4978   0.0198
  -6.250  -0.2576   0.05495   0.05085  -0.0450   0.4968   0.0210
  -6.000  -0.2475   0.05132   0.04709  -0.0455   0.4955   0.0215
  -5.750  -0.2359   0.04769   0.04329  -0.0455   0.4941   0.0220
  -5.500  -0.2144   0.04384   0.03908  -0.0447   0.4931   0.0242
  -5.250  -0.2020   0.04051   0.03550  -0.0433   0.4919   0.0243
  -5.000  -0.2040   0.03354   0.02822  -0.0410   0.4910   0.0254
  -4.750  -0.1866   0.03153   0.02608  -0.0399   0.4895   0.0259
  -4.500  -0.1677   0.02997   0.02441  -0.0389   0.4882   0.0267
  -4.250  -0.1473   0.02878   0.02310  -0.0379   0.4868   0.0285
  -4.000  -0.1336   0.02316   0.01674  -0.0336   0.4859   0.0228
  -3.750  -0.1168   0.01932   0.01233  -0.0308   0.4849   0.0207
  -3.500  -0.0932   0.01769   0.01039  -0.0295   0.4837   0.0212
  -3.250  -0.0678   0.01670   0.00919  -0.0286   0.4825   0.0225
  -3.000  -0.0418   0.01591   0.00820  -0.0279   0.4813   0.0235
  -2.750  -0.0167   0.01483   0.00695  -0.0272   0.4798   0.0260
  -2.500   0.0091   0.01436   0.00645  -0.0267   0.4785   0.0278
  -2.250   0.0353   0.01388   0.00593  -0.0261   0.4774   0.0297
  -2.000   0.0615   0.01353   0.00552  -0.0256   0.4764   0.0321
  -1.750   0.0866   0.01301   0.00495  -0.0248   0.4753   0.0346
  -1.500   0.1115   0.01259   0.00452  -0.0241   0.4742   0.0383
  -1.250   0.1374   0.01237   0.00427  -0.0236   0.4730   0.0417
  -1.000   0.1636   0.01221   0.00407  -0.0231   0.4718   0.0453
  -0.750   0.1889   0.01192   0.00377  -0.0224   0.4707   0.0523
  -0.500   0.2150   0.01175   0.00359  -0.0219   0.4694   0.0642
  -0.250   0.2379   0.01120   0.00347  -0.0210   0.4682   0.1899
   0.000   0.2516   0.01007   0.00344  -0.0186   0.4671   0.5433
   0.250   0.4409   0.00970   0.00399  -0.0531   0.4644   0.9966
   0.500   0.4827   0.00970   0.00394  -0.0561   0.4634   1.0000
   0.750   0.5080   0.00976   0.00396  -0.0556   0.4625   1.0000
   1.000   0.5332   0.00982   0.00399  -0.0551   0.4614   1.0000
   1.250   0.5586   0.00989   0.00404  -0.0546   0.4603   1.0000
   1.500   0.5839   0.00995   0.00407  -0.0542   0.4586   1.0000
   1.750   0.6094   0.01004   0.00414  -0.0537   0.4574   1.0000
   2.000   0.6349   0.01010   0.00418  -0.0533   0.4558   1.0000
   2.250   0.6605   0.01017   0.00421  -0.0529   0.4541   1.0000
   2.500   0.6862   0.01027   0.00427  -0.0525   0.4527   1.0000
   2.750   0.7119   0.01041   0.00437  -0.0521   0.4515   1.0000
   3.000   0.7375   0.01066   0.00458  -0.0517   0.4497   1.0000
   3.250   0.7628   0.01076   0.00471  -0.0513   0.4485   1.0000
   3.500   0.7881   0.01083   0.00481  -0.0509   0.4469   1.0000
   3.750   0.8134   0.01090   0.00492  -0.0504   0.4449   1.0000
   4.000   0.8388   0.01096   0.00500  -0.0500   0.4427   1.0000
   4.250   0.8643   0.01104   0.00508  -0.0496   0.4408   1.0000
   4.500   0.8900   0.01112   0.00517  -0.0492   0.4389   1.0000
   4.750   0.9157   0.01124   0.00526  -0.0489   0.4370   1.0000
   5.000   0.9411   0.01149   0.00549  -0.0486   0.4345   1.0000
   5.250   0.9660   0.01149   0.00558  -0.0480   0.4322   1.0000
   5.500   0.9910   0.01158   0.00575  -0.0476   0.4301   1.0000
   5.750   1.0162   0.01169   0.00591  -0.0472   0.4280   1.0000
   6.000   1.0415   0.01179   0.00605  -0.0468   0.4260   1.0000
   6.250   1.0670   0.01189   0.00617  -0.0465   0.4241   1.0000
   6.500   1.0927   0.01201   0.00631  -0.0462   0.4221   1.0000
   6.750   1.1179   0.01224   0.00655  -0.0458   0.4196   1.0000
   7.000   1.1422   0.01230   0.00674  -0.0453   0.4172   1.0000
   7.250   1.1667   0.01238   0.00692  -0.0448   0.4144   1.0000
   7.500   1.1917   0.01244   0.00707  -0.0444   0.4117   1.0000
   7.750   1.2169   0.01246   0.00712  -0.0440   0.4087   1.0000
   8.000   1.2418   0.01244   0.00712  -0.0435   0.4042   1.0000
   8.250   1.2656   0.01212   0.00693  -0.0427   0.3962   1.0000
   8.500   1.2899   0.01190   0.00678  -0.0421   0.3880   1.0000
   8.750   1.3143   0.01167   0.00663  -0.0415   0.3754   1.0000
   9.000   1.3382   0.01159   0.00658  -0.0409   0.3541   1.0000
   9.250   1.3578   0.01193   0.00679  -0.0398   0.3227   1.0000
   9.500   1.3704   0.01289   0.00752  -0.0379   0.2779   1.0000
   9.750   1.3760   0.01442   0.00876  -0.0351   0.2252   1.0000
  10.000   1.3782   0.01608   0.01016  -0.0321   0.1764   1.0000
  10.250   1.3602   0.01882   0.01243  -0.0267   0.1056   1.0000
  10.500   1.3355   0.02137   0.01476  -0.0207   0.0665   1.0000
  10.750   1.3145   0.02443   0.01779  -0.0178   0.0477   1.0000
  11.000   1.2941   0.02932   0.02264  -0.0183   0.0288   1.0000
  11.250   1.2795   0.03375   0.02709  -0.0186   0.0206   1.0000
  11.500   1.2729   0.03722   0.03065  -0.0187   0.0178   1.0000
  11.750   1.2659   0.04065   0.03414  -0.0187   0.0152   1.0000
  12.000   1.2520   0.04482   0.03840  -0.0186   0.0125   1.0000
  12.250   1.2467   0.04807   0.04175  -0.0186   0.0128   1.0000
  12.500   1.2466   0.05075   0.04451  -0.0186   0.0123   1.0000
  12.750   1.2411   0.05404   0.04788  -0.0186   0.0112   1.0000
  13.000   1.2356   0.05746   0.05137  -0.0187   0.0105   1.0000
  13.250   1.2281   0.06123   0.05520  -0.0190   0.0097   1.0000
  13.500   1.2230   0.06484   0.05890  -0.0194   0.0095   1.0000
  13.750   1.2163   0.06871   0.06286  -0.0198   0.0094   1.0000
  14.000   1.2100   0.07262   0.06686  -0.0203   0.0087   1.0000
  14.250   1.2085   0.07591   0.07023  -0.0207   0.0086   1.0000
  14.500   1.2072   0.07929   0.07369  -0.0212   0.0080   1.0000
  14.750   1.2084   0.08228   0.07677  -0.0217   0.0081   1.0000
  15.000   1.2037   0.08609   0.08065  -0.0222   0.0081   1.0000
  15.250   1.2017   0.08958   0.08422  -0.0227   0.0079   1.0000
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