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WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il)
Reynolds number: 500,000
Max Cl/Cd: 102.34 at α=10.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx77w153-il-500000.txt
Download as CSV file: xf-fx77w153-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 77-W-153 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3860   0.10526   0.10128  -0.0011   0.4656   0.0265
  -9.500  -0.3887   0.09945   0.09547  -0.0054   0.4636   0.0266
  -9.250  -0.3912   0.09365   0.08967  -0.0096   0.4616   0.0267
  -9.000  -0.3929   0.08790   0.08391  -0.0140   0.4593   0.0267
  -8.750  -0.3957   0.08324   0.07928  -0.0158   0.4569   0.0269
  -8.500  -0.3953   0.07897   0.07502  -0.0189   0.4543   0.0270
  -8.250  -0.3997   0.07316   0.06921  -0.0252   0.4524   0.0271
  -8.000  -0.4037   0.06863   0.06463  -0.0279   0.4502   0.0272
  -7.750  -0.4018   0.06440   0.06032  -0.0301   0.4479   0.0274
  -7.500  -0.3976   0.06044   0.05626  -0.0317   0.4457   0.0276
  -7.250  -0.3913   0.05663   0.05231  -0.0329   0.4435   0.0278
  -7.000  -0.3834   0.05285   0.04839  -0.0336   0.4414   0.0281
  -6.750  -0.3739   0.04902   0.04440  -0.0339   0.4398   0.0286
  -6.500  -0.3632   0.04511   0.04029  -0.0337   0.4381   0.0291
  -6.250  -0.3868   0.02862   0.02219  -0.0285   0.4389   0.0221
  -6.000  -0.3682   0.02613   0.01947  -0.0275   0.4368   0.0217
  -5.750  -0.3481   0.02379   0.01682  -0.0263   0.4347   0.0212
  -5.500  -0.3263   0.02168   0.01436  -0.0251   0.4328   0.0208
  -5.250  -0.3025   0.02005   0.01244  -0.0242   0.4309   0.0207
  -5.000  -0.2772   0.01887   0.01102  -0.0235   0.4291   0.0208
  -4.750  -0.2514   0.01796   0.00991  -0.0230   0.4272   0.0210
  -4.500  -0.2251   0.01723   0.00903  -0.0224   0.4255   0.0214
  -4.250  -0.1983   0.01658   0.00828  -0.0220   0.4242   0.0219
  -4.000  -0.1711   0.01611   0.00770  -0.0216   0.4227   0.0225
  -3.750  -0.1454   0.01541   0.00701  -0.0211   0.4212   0.0233
  -3.500  -0.1184   0.01505   0.00664  -0.0208   0.4197   0.0246
  -3.250  -0.0911   0.01475   0.00627  -0.0205   0.4184   0.0263
  -3.000  -0.0656   0.01415   0.00567  -0.0199   0.4171   0.0288
  -2.750  -0.0395   0.01371   0.00520  -0.0194   0.4157   0.0328
  -2.500  -0.0121   0.01354   0.00499  -0.0192   0.4144   0.0362
  -2.250   0.0152   0.01336   0.00481  -0.0190   0.4133   0.0390
  -2.000   0.0433   0.01335   0.00477  -0.0189   0.4123   0.0419
  -1.750   0.0709   0.01327   0.00467  -0.0188   0.4111   0.0444
  -1.500   0.0986   0.01330   0.00466  -0.0187   0.4098   0.0470
  -1.250   0.1268   0.01328   0.00462  -0.0186   0.4090   0.0493
  -1.000   0.1544   0.01311   0.00446  -0.0184   0.4083   0.0515
  -0.750   0.1822   0.01300   0.00435  -0.0183   0.4076   0.0544
  -0.500   0.2102   0.01291   0.00427  -0.0182   0.4068   0.0596
  -0.250   0.2376   0.01272   0.00421  -0.0180   0.4056   0.0814
   0.000   0.2625   0.01220   0.00414  -0.0176   0.4043   0.2123
   0.250   0.2859   0.01158   0.00411  -0.0170   0.4030   0.3962
   0.500   0.3064   0.01090   0.00411  -0.0157   0.4018   0.6002
   0.750   0.3529   0.01011   0.00438  -0.0190   0.4005   0.9160
   1.000   0.4008   0.01038   0.00459  -0.0228   0.3990   0.9573
   1.250   0.4393   0.01059   0.00472  -0.0248   0.3975   0.9729
   1.500   0.4842   0.01082   0.00484  -0.0282   0.3956   0.9828
   1.750   0.5358   0.01120   0.00512  -0.0332   0.3931   0.9916
   2.000   0.5931   0.01115   0.00505  -0.0393   0.3916   0.9979
   2.250   0.6297   0.01118   0.00506  -0.0412   0.3900   1.0000
   2.500   0.6561   0.01125   0.00512  -0.0410   0.3887   1.0000
   2.750   0.6824   0.01133   0.00518  -0.0407   0.3874   1.0000
   3.000   0.7088   0.01142   0.00526  -0.0405   0.3860   1.0000
   3.250   0.7351   0.01151   0.00532  -0.0402   0.3845   1.0000
   3.500   0.7613   0.01159   0.00538  -0.0400   0.3830   1.0000
   3.750   0.7876   0.01169   0.00545  -0.0397   0.3816   1.0000
   4.000   0.8138   0.01182   0.00554  -0.0394   0.3802   1.0000
   4.250   0.8400   0.01202   0.00570  -0.0392   0.3786   1.0000
   4.500   0.8660   0.01228   0.00595  -0.0390   0.3770   1.0000
   4.750   0.8919   0.01235   0.00606  -0.0387   0.3757   1.0000
   5.000   0.9177   0.01243   0.00618  -0.0384   0.3741   1.0000
   5.250   0.9435   0.01251   0.00628  -0.0380   0.3721   1.0000
   5.500   0.9693   0.01259   0.00637  -0.0377   0.3700   1.0000
   5.750   0.9951   0.01268   0.00646  -0.0374   0.3681   1.0000
   6.000   1.0209   0.01278   0.00655  -0.0371   0.3663   1.0000
   6.250   1.0466   0.01291   0.00667  -0.0368   0.3645   1.0000
   6.500   1.0722   0.01321   0.00693  -0.0366   0.3622   1.0000
   6.750   1.0972   0.01333   0.00712  -0.0362   0.3604   1.0000
   7.000   1.1222   0.01343   0.00729  -0.0358   0.3584   1.0000
   7.250   1.1472   0.01354   0.00745  -0.0354   0.3560   1.0000
   7.500   1.1723   0.01360   0.00753  -0.0350   0.3534   1.0000
   7.750   1.1974   0.01365   0.00758  -0.0346   0.3507   1.0000
   8.000   1.2224   0.01378   0.00769  -0.0342   0.3480   1.0000
   8.250   1.2467   0.01399   0.00792  -0.0338   0.3449   1.0000
   8.500   1.2706   0.01398   0.00801  -0.0332   0.3416   1.0000
   8.750   1.2948   0.01397   0.00807  -0.0327   0.3377   1.0000
   9.000   1.3192   0.01396   0.00807  -0.0322   0.3341   1.0000
   9.250   1.3429   0.01407   0.00816  -0.0316   0.3302   1.0000
   9.500   1.3669   0.01406   0.00829  -0.0311   0.3255   1.0000
   9.750   1.3910   0.01407   0.00836  -0.0306   0.3203   1.0000
  10.000   1.4146   0.01411   0.00842  -0.0300   0.3155   1.0000
  10.250   1.4384   0.01420   0.00859  -0.0296   0.3092   1.0000
  10.750   1.4829   0.01449   0.00891  -0.0282   0.2961   1.0000
  11.000   1.5024   0.01480   0.00918  -0.0271   0.2889   1.0000
  11.250   1.5224   0.01514   0.00957  -0.0262   0.2822   1.0000
  11.500   1.5399   0.01559   0.01001  -0.0249   0.2752   1.0000
  11.750   1.5581   0.01600   0.01047  -0.0237   0.2688   1.0000
  12.000   1.5755   0.01644   0.01095  -0.0225   0.2608   1.0000
  12.250   1.5910   0.01697   0.01150  -0.0210   0.2525   1.0000
  12.750   1.6149   0.01833   0.01288  -0.0175   0.2360   1.0000
  13.000   1.6184   0.01926   0.01380  -0.0146   0.2293   1.0000
  13.250   1.6267   0.02010   0.01471  -0.0127   0.2231   1.0000
  13.500   1.6306   0.02136   0.01601  -0.0109   0.2155   1.0000
  13.750   1.6348   0.02285   0.01756  -0.0097   0.2081   1.0000
  14.000   1.6333   0.02514   0.01989  -0.0091   0.1984   1.0000
  14.250   1.6285   0.02821   0.02302  -0.0094   0.1899   1.0000
  14.500   1.6144   0.03269   0.02756  -0.0105   0.1833   1.0000
  14.750   1.6031   0.03689   0.03185  -0.0113   0.1772   1.0000
  15.000   1.5832   0.04197   0.03701  -0.0121   0.1723   1.0000
  15.250   1.5596   0.04735   0.04246  -0.0128   0.1687   1.0000
  15.500   1.5466   0.05151   0.04671  -0.0132   0.1619   1.0000
  15.750   1.5222   0.05691   0.05216  -0.0138   0.1547   1.0000
  16.000   1.4994   0.06228   0.05756  -0.0146   0.1459   1.0000
  16.250   1.4743   0.06817   0.06345  -0.0156   0.1378   1.0000
  16.500   1.4521   0.07381   0.06910  -0.0167   0.1304   1.0000
  16.750   1.4354   0.07888   0.07419  -0.0177   0.1224   1.0000
  17.000   1.4155   0.08443   0.07974  -0.0188   0.1130   1.0000
  17.250   1.3947   0.09023   0.08551  -0.0201   0.1013   1.0000
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