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FX 77-W-121 (fx77w121-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: FX 77-W-121 (fx77w121-il)
Reynolds number: 1,000,000
Max Cl/Cd: 145.32 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx77w121-il-1000000-n5.txt
Download as CSV file: xf-fx77w121-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3062   0.09783   0.09420  -0.0272   0.4509   0.0048
  -9.750  -0.2962   0.09593   0.09229  -0.0283   0.4493   0.0056
  -8.250  -0.5619   0.02156   0.01648  -0.0402   0.4530   0.0059
  -8.000  -0.5428   0.02031   0.01501  -0.0389   0.4511   0.0062
  -7.750  -0.5256   0.01870   0.01311  -0.0372   0.4495   0.0063
  -7.500  -0.5066   0.01731   0.01147  -0.0356   0.4484   0.0063
  -7.250  -0.4819   0.01697   0.01104  -0.0350   0.4472   0.0064
  -7.000  -0.4597   0.01610   0.01000  -0.0339   0.4459   0.0065
  -6.750  -0.4381   0.01511   0.00880  -0.0327   0.4445   0.0067
  -6.500  -0.4153   0.01432   0.00787  -0.0317   0.4432   0.0070
  -6.250  -0.3904   0.01393   0.00740  -0.0310   0.4417   0.0073
  -6.000  -0.3659   0.01344   0.00681  -0.0303   0.4404   0.0074
  -5.750  -0.3410   0.01303   0.00632  -0.0296   0.4392   0.0076
  -5.500  -0.3151   0.01279   0.00603  -0.0291   0.4380   0.0080
  -5.250  -0.2897   0.01248   0.00563  -0.0285   0.4368   0.0085
  -5.000  -0.2642   0.01218   0.00525  -0.0279   0.4356   0.0088
  -4.750  -0.2386   0.01187   0.00488  -0.0273   0.4346   0.0092
  -4.500  -0.2129   0.01156   0.00450  -0.0267   0.4340   0.0093
  -4.250  -0.1876   0.01119   0.00407  -0.0260   0.4332   0.0101
  -4.000  -0.1614   0.01098   0.00386  -0.0256   0.4324   0.0109
  -3.750  -0.1353   0.01076   0.00359  -0.0251   0.4315   0.0113
  -3.500  -0.1089   0.01058   0.00338  -0.0246   0.4307   0.0122
  -3.250  -0.0823   0.01044   0.00320  -0.0242   0.4299   0.0129
  -3.000  -0.0563   0.01021   0.00295  -0.0237   0.4292   0.0139
  -2.750  -0.0296   0.01009   0.00282  -0.0233   0.4283   0.0154
  -2.500  -0.0030   0.00997   0.00269  -0.0230   0.4274   0.0166
  -2.250   0.0237   0.00986   0.00255  -0.0226   0.4264   0.0176
  -2.000   0.0501   0.00971   0.00238  -0.0222   0.4255   0.0194
  -1.750   0.0767   0.00960   0.00226  -0.0218   0.4246   0.0212
  -1.500   0.1036   0.00953   0.00218  -0.0215   0.4238   0.0231
  -1.250   0.1305   0.00947   0.00209  -0.0212   0.4230   0.0242
  -1.000   0.1570   0.00936   0.00196  -0.0208   0.4221   0.0271
  -0.750   0.1836   0.00929   0.00189  -0.0205   0.4213   0.0301
  -0.500   0.2104   0.00926   0.00183  -0.0202   0.4203   0.0329
  -0.250   0.2372   0.00919   0.00178  -0.0199   0.4197   0.0386
   0.000   0.2640   0.00910   0.00173  -0.0196   0.4191   0.0511
   0.250   0.2905   0.00898   0.00169  -0.0192   0.4185   0.0795
   0.500   0.3165   0.00881   0.00167  -0.0188   0.4178   0.1297
   0.750   0.3418   0.00861   0.00166  -0.0183   0.4172   0.2015
   1.000   0.3657   0.00829   0.00167  -0.0176   0.4165   0.3228
   1.250   0.3877   0.00787   0.00169  -0.0165   0.4159   0.4823
   1.500   0.3990   0.00704   0.00168  -0.0131   0.4152   0.7503
   2.000   0.5962   0.00713   0.00223  -0.0442   0.4120   0.9914
   2.250   0.6383   0.00719   0.00225  -0.0473   0.4105   0.9944
   2.500   0.6725   0.00725   0.00229  -0.0488   0.4095   0.9962
   2.750   0.7064   0.00728   0.00229  -0.0502   0.4082   0.9975
   3.000   0.7361   0.00734   0.00232  -0.0507   0.4061   0.9982
   3.250   0.7658   0.00738   0.00235  -0.0511   0.4047   0.9988
   3.500   0.7956   0.00739   0.00238  -0.0516   0.4034   0.9994
   3.750   0.8254   0.00739   0.00239  -0.0521   0.4012   0.9998
   4.000   0.8532   0.00741   0.00242  -0.0522   0.3994   1.0000
   4.250   0.8791   0.00745   0.00247  -0.0519   0.3976   1.0000
   4.500   0.9049   0.00749   0.00252  -0.0515   0.3954   1.0000
   4.750   0.9306   0.00754   0.00258  -0.0511   0.3937   1.0000
   5.000   0.9561   0.00761   0.00265  -0.0508   0.3921   1.0000
   5.250   0.9817   0.00769   0.00274  -0.0504   0.3905   1.0000
   5.500   1.0076   0.00773   0.00283  -0.0501   0.3892   1.0000
   5.750   1.0335   0.00778   0.00292  -0.0498   0.3874   1.0000
   6.000   1.0595   0.00782   0.00300  -0.0495   0.3844   1.0000
   6.250   1.0852   0.00788   0.00310  -0.0492   0.3818   1.0000
   6.500   1.1108   0.00795   0.00319  -0.0489   0.3792   1.0000
   6.750   1.1363   0.00803   0.00329  -0.0485   0.3765   1.0000
   7.000   1.1621   0.00808   0.00340  -0.0483   0.3712   1.0000
   7.250   1.1873   0.00817   0.00349  -0.0479   0.3626   1.0000
   7.500   1.2109   0.00839   0.00362  -0.0473   0.3395   1.0000
   7.750   1.2321   0.00884   0.00394  -0.0465   0.3093   1.0000
   8.000   1.2458   0.00999   0.00474  -0.0446   0.2471   1.0000
   8.250   1.2620   0.01088   0.00542  -0.0432   0.2089   1.0000
   8.500   1.2772   0.01180   0.00615  -0.0416   0.1714   1.0000
   8.750   1.2907   0.01281   0.00696  -0.0397   0.1339   1.0000
   9.000   1.2965   0.01432   0.00818  -0.0370   0.0834   1.0000
   9.250   1.3006   0.01581   0.00945  -0.0339   0.0442   1.0000
   9.500   1.3042   0.01717   0.01067  -0.0309   0.0184   1.0000
   9.750   1.3150   0.01798   0.01149  -0.0287   0.0123   1.0000
  10.000   1.3252   0.01880   0.01233  -0.0266   0.0095   1.0000
  10.250   1.3323   0.01963   0.01321  -0.0240   0.0075   1.0000
  10.500   1.3303   0.02062   0.01425  -0.0203   0.0064   1.0000
  10.750   1.3312   0.02208   0.01578  -0.0184   0.0060   1.0000
  11.000   1.3342   0.02416   0.01794  -0.0182   0.0052   1.0000
  11.250   1.3393   0.02642   0.02028  -0.0185   0.0051   1.0000
  11.500   1.3433   0.02888   0.02281  -0.0189   0.0049   1.0000
  11.750   1.3417   0.03192   0.02591  -0.0192   0.0041   1.0000
  12.000   1.3423   0.03464   0.02871  -0.0194   0.0037   1.0000
  12.250   1.3434   0.03725   0.03139  -0.0194   0.0038   1.0000
  12.500   1.3459   0.03965   0.03384  -0.0195   0.0034   1.0000
  12.750   1.3428   0.04266   0.03692  -0.0195   0.0032   1.0000
  13.000   1.3402   0.04559   0.03991  -0.0194   0.0030   1.0000
  13.250   1.3366   0.04862   0.04301  -0.0195   0.0026   1.0000
  13.500   1.3366   0.05128   0.04574  -0.0195   0.0028   1.0000
  13.750   1.3350   0.05416   0.04868  -0.0196   0.0026   1.0000
  14.000   1.3274   0.05789   0.05250  -0.0199   0.0025   1.0000
  14.250   1.3300   0.06045   0.05512  -0.0201   0.0024   1.0000
  14.500   1.3309   0.06330   0.05803  -0.0204   0.0022   1.0000
  14.750   1.3350   0.06577   0.06054  -0.0208   0.0023   1.0000
  15.000   1.3331   0.06899   0.06383  -0.0211   0.0023   1.0000
  15.250   1.3296   0.07251   0.06745  -0.0217   0.0023   1.0000
  15.500   1.3340   0.07502   0.07000  -0.0220   0.0020   1.0000
  15.750   1.3292   0.07880   0.07386  -0.0227   0.0021   1.0000
  16.000   1.3305   0.08175   0.07687  -0.0232   0.0020   1.0000
  16.250   1.3282   0.08526   0.08046  -0.0239   0.0019   1.0000
  16.500   1.3283   0.08847   0.08374  -0.0246   0.0018   1.0000
  16.750   1.3248   0.09225   0.08760  -0.0254   0.0018   1.0000
  17.000   1.3241   0.09562   0.09103  -0.0262   0.0018   1.0000
  17.250   1.3222   0.09923   0.09470  -0.0271   0.0016   1.0000
  17.500   1.3182   0.10319   0.09874  -0.0281   0.0016   1.0000
  17.750   1.3159   0.10696   0.10258  -0.0292   0.0016   1.0000
  18.000   1.3108   0.11120   0.10690  -0.0304   0.0016   1.0000
  18.250   1.3098   0.11481   0.11059  -0.0315   0.0017   1.0000
  18.500   1.3014   0.11963   0.11548  -0.0331   0.0014   1.0000
  18.750   1.3007   0.12328   0.11921  -0.0343   0.0015   1.0000
  19.000   1.2960   0.12764   0.12366  -0.0358   0.0016   1.0000
  19.250   1.2836   0.13339   0.12951  -0.0380   0.0015   1.0000
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