Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

WORTMANN FX 77-W-258 AIRFOIL (fx77w258-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 77-W-258 AIRFOIL (fx77w258-il)
Reynolds number: 500,000
Max Cl/Cd: 83.18 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx77w258-il-500000-n5.txt
Download as CSV file: xf-fx77w258-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 77-W-258 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -0.9432   0.11393   0.10778  -0.0185   0.5087   0.0062
 -19.500  -0.9558   0.10793   0.10165  -0.0217   0.5060   0.0062
 -19.250  -0.9667   0.10229   0.09588  -0.0246   0.5032   0.0062
 -19.000  -0.9760   0.09701   0.09047  -0.0272   0.5001   0.0062
 -18.750  -0.9832   0.09219   0.08551  -0.0295   0.4970   0.0062
 -18.500  -0.9887   0.08766   0.08087  -0.0315   0.4938   0.0061
 -18.250  -0.9925   0.08348   0.07657  -0.0333   0.4910   0.0061
 -18.000  -0.9944   0.07966   0.07265  -0.0348   0.4886   0.0062
 -17.750  -0.9954   0.07603   0.06892  -0.0362   0.4859   0.0062
 -17.500  -0.9951   0.07265   0.06544  -0.0374   0.4829   0.0062
 -17.250  -0.9935   0.06947   0.06216  -0.0384   0.4799   0.0062
 -17.000  -0.9899   0.06664   0.05923  -0.0393   0.4769   0.0062
 -16.750  -0.9863   0.06384   0.05634  -0.0400   0.4740   0.0062
 -16.250  -0.9751   0.05890   0.05122  -0.0411   0.4694   0.0062
 -16.000  -0.9686   0.05660   0.04884  -0.0416   0.4676   0.0062
 -15.750  -0.9605   0.05453   0.04670  -0.0418   0.4657   0.0062
 -15.500  -0.9522   0.05254   0.04463  -0.0421   0.4638   0.0062
 -15.250  -0.9432   0.05064   0.04266  -0.0422   0.4619   0.0063
 -15.000  -0.9331   0.04890   0.04085  -0.0423   0.4600   0.0063
 -14.750  -0.9229   0.04719   0.03907  -0.0423   0.4582   0.0063
 -14.500  -0.9118   0.04562   0.03743  -0.0423   0.4564   0.0063
 -14.250  -0.9002   0.04413   0.03587  -0.0422   0.4545   0.0063
 -14.000  -0.8884   0.04267   0.03434  -0.0421   0.4525   0.0064
 -13.750  -0.8754   0.04136   0.03297  -0.0419   0.4506   0.0064
 -13.500  -0.8620   0.04011   0.03168  -0.0416   0.4495   0.0064
 -13.250  -0.8488   0.03888   0.03041  -0.0414   0.4484   0.0064
 -13.000  -0.8357   0.03769   0.02918  -0.0410   0.4472   0.0065
 -12.750  -0.8213   0.03661   0.02806  -0.0407   0.4460   0.0065
 -12.500  -0.8066   0.03557   0.02699  -0.0403   0.4449   0.0066
 -12.250  -0.7918   0.03455   0.02593  -0.0399   0.4437   0.0067
 -12.000  -0.7768   0.03354   0.02489  -0.0395   0.4425   0.0068
 -11.750  -0.7610   0.03261   0.02392  -0.0391   0.4413   0.0069
 -11.500  -0.7448   0.03172   0.02299  -0.0387   0.4401   0.0070
 -11.250  -0.7286   0.03083   0.02208  -0.0383   0.4389   0.0071
 -11.000  -0.7121   0.02997   0.02119  -0.0379   0.4377   0.0073
 -10.750  -0.6949   0.02917   0.02039  -0.0375   0.4365   0.0076
 -10.500  -0.6779   0.02837   0.01958  -0.0371   0.4354   0.0078
 -10.250  -0.6611   0.02756   0.01875  -0.0366   0.4342   0.0080
 -10.000  -0.6435   0.02680   0.01797  -0.0362   0.4329   0.0117
  -9.750  -0.6241   0.02618   0.01731  -0.0359   0.4316   0.0122
  -9.500  -0.6044   0.02558   0.01668  -0.0356   0.4304   0.0126
  -9.250  -0.5847   0.02495   0.01603  -0.0353   0.4299   0.0133
  -9.000  -0.5648   0.02433   0.01540  -0.0350   0.4294   0.0139
  -8.750  -0.5445   0.02376   0.01481  -0.0347   0.4287   0.0144
  -8.500  -0.5242   0.02318   0.01421  -0.0343   0.4280   0.0148
  -8.250  -0.5040   0.02263   0.01365  -0.0340   0.4271   0.0151
  -8.000  -0.4857   0.02212   0.01312  -0.0333   0.4262   0.0154
  -7.750  -0.4712   0.02155   0.01255  -0.0321   0.4252   0.0157
  -7.500  -0.4527   0.02099   0.01197  -0.0316   0.4241   0.0160
  -7.250  -0.4309   0.02045   0.01142  -0.0317   0.4231   0.0166
  -7.000  -0.4071   0.01996   0.01092  -0.0320   0.4220   0.0171
  -6.750  -0.3820   0.01953   0.01046  -0.0325   0.4210   0.0174
  -6.500  -0.3561   0.01917   0.01008  -0.0329   0.4202   0.0177
  -6.250  -0.3296   0.01886   0.00974  -0.0332   0.4193   0.0180
  -6.000  -0.3026   0.01858   0.00944  -0.0336   0.4184   0.0183
  -5.750  -0.2754   0.01828   0.00913  -0.0340   0.4176   0.0187
  -5.500  -0.2477   0.01800   0.00883  -0.0345   0.4166   0.0192
  -5.250  -0.2196   0.01774   0.00855  -0.0350   0.4156   0.0197
  -5.000  -0.1910   0.01751   0.00831  -0.0355   0.4145   0.0202
  -4.750  -0.1621   0.01731   0.00809  -0.0361   0.4134   0.0208
  -4.500  -0.1329   0.01714   0.00791  -0.0367   0.4125   0.0217
  -4.250  -0.1036   0.01697   0.00776  -0.0374   0.4115   0.0235
  -4.000  -0.0738   0.01678   0.00761  -0.0381   0.4108   0.0322
  -3.750  -0.0435   0.01665   0.00748  -0.0388   0.4103   0.0354
  -3.500  -0.0130   0.01651   0.00735  -0.0396   0.4098   0.0384
  -3.250   0.0175   0.01632   0.00719  -0.0404   0.4092   0.0414
  -3.000   0.0481   0.01607   0.00702  -0.0414   0.4086   0.0492
  -2.750   0.0790   0.01590   0.00690  -0.0423   0.4080   0.0681
  -2.500   0.1101   0.01566   0.00676  -0.0433   0.4073   0.0811
  -2.250   0.1414   0.01550   0.00665  -0.0443   0.4066   0.1049
  -2.000   0.1730   0.01523   0.00652  -0.0455   0.4058   0.1355
  -1.750   0.2046   0.01511   0.00645  -0.0465   0.4051   0.1520
  -1.500   0.2366   0.01485   0.00633  -0.0478   0.4043   0.1918
  -1.250   0.2693   0.01449   0.00618  -0.0494   0.4035   0.2467
  -1.000   0.3028   0.01405   0.00599  -0.0513   0.4027   0.3186
  -0.750   0.3384   0.01331   0.00568  -0.0539   0.4018   0.4385
  -0.500   0.3728   0.01289   0.00569  -0.0559   0.4010   0.5402
  -0.250   0.4046   0.01298   0.00587  -0.0567   0.4002   0.5742
   0.000   0.4358   0.01316   0.00611  -0.0573   0.3994   0.5922
   0.250   0.4671   0.01333   0.00627  -0.0580   0.3985   0.6061
   0.500   0.4989   0.01345   0.00632  -0.0588   0.3975   0.6148
   0.750   0.5301   0.01356   0.00641  -0.0595   0.3965   0.6187
   1.000   0.5610   0.01369   0.00651  -0.0602   0.3953   0.6217
   1.250   0.5919   0.01384   0.00664  -0.0609   0.3941   0.6251
   1.500   0.6228   0.01403   0.00679  -0.0616   0.3929   0.6288
   1.750   0.6538   0.01421   0.00694  -0.0623   0.3920   0.6325
   2.000   0.6851   0.01436   0.00707  -0.0631   0.3915   0.6357
   2.250   0.7156   0.01447   0.00722  -0.0638   0.3909   0.6389
   2.500   0.7459   0.01462   0.00741  -0.0644   0.3902   0.6418
   2.750   0.7762   0.01478   0.00761  -0.0649   0.3895   0.6448
   3.000   0.8065   0.01493   0.00778  -0.0656   0.3887   0.6474
   3.250   0.8369   0.01508   0.00794  -0.0662   0.3878   0.6501
   3.500   0.8673   0.01522   0.00809  -0.0669   0.3866   0.6530
   3.750   0.8978   0.01535   0.00822  -0.0676   0.3854   0.6553
   4.000   0.9282   0.01547   0.00833  -0.0684   0.3840   0.6570
   4.250   0.9583   0.01553   0.00840  -0.0690   0.3828   0.6584
   4.500   0.9883   0.01559   0.00848  -0.0697   0.3815   0.6594
   4.750   1.0182   0.01566   0.00855  -0.0704   0.3801   0.6602
   5.000   1.0480   0.01573   0.00861  -0.0710   0.3786   0.6611
   5.250   1.0774   0.01581   0.00869  -0.0716   0.3769   0.6621
   5.500   1.1065   0.01595   0.00880  -0.0722   0.3751   0.6631
   5.750   1.1355   0.01609   0.00896  -0.0727   0.3733   0.6641
   6.000   1.1647   0.01617   0.00910  -0.0734   0.3717   0.6650
   6.250   1.1939   0.01625   0.00923  -0.0740   0.3694   0.6658
   6.500   1.2229   0.01633   0.00934  -0.0746   0.3666   0.6665
   6.750   1.2517   0.01642   0.00944  -0.0751   0.3637   0.6672
   7.000   1.2801   0.01650   0.00952  -0.0756   0.3607   0.6680
   7.250   1.3079   0.01661   0.00962  -0.0760   0.3579   0.6687
   7.500   1.3353   0.01677   0.00977  -0.0764   0.3555   0.6694
   7.750   1.3630   0.01694   0.01000  -0.0769   0.3536   0.6702
   8.000   1.3904   0.01713   0.01024  -0.0773   0.3516   0.6709
   8.250   1.4172   0.01732   0.01047  -0.0776   0.3492   0.6716
   8.500   1.4435   0.01753   0.01070  -0.0779   0.3467   0.6723
   8.750   1.4691   0.01774   0.01093  -0.0781   0.3440   0.6729
   9.000   1.4938   0.01797   0.01118  -0.0781   0.3414   0.6736
   9.250   1.5172   0.01824   0.01145  -0.0780   0.3390   0.6742
   9.500   1.5406   0.01854   0.01179  -0.0779   0.3368   0.6748
   9.750   1.5626   0.01887   0.01215  -0.0776   0.3344   0.6754
  10.000   1.5823   0.01924   0.01256  -0.0770   0.3316   0.6759
  10.250   1.5974   0.01970   0.01304  -0.0757   0.3286   0.6764
  10.500   1.6053   0.02035   0.01370  -0.0734   0.3255   0.6769
  10.750   1.6146   0.02128   0.01465  -0.0719   0.3221   0.6774
  11.000   1.6284   0.02217   0.01561  -0.0713   0.3192   0.6778
  11.250   1.6390   0.02335   0.01685  -0.0707   0.3156   0.6782
  11.500   1.6463   0.02489   0.01845  -0.0701   0.3120   0.6788
  11.750   1.6487   0.02697   0.02058  -0.0697   0.3084   0.6795
  12.000   1.6461   0.02966   0.02333  -0.0695   0.3051   0.6802
  12.250   1.6512   0.03180   0.02559  -0.0696   0.3028   0.6811
  12.500   1.6492   0.03469   0.02859  -0.0696   0.2989   0.6819
  12.750   1.6315   0.03920   0.03323  -0.0695   0.2932   0.6826
  13.000   1.5964   0.04543   0.03956  -0.0690   0.2883   0.6832
  13.250   1.5625   0.05154   0.04579  -0.0685   0.2832   0.6837
  13.500   1.5223   0.05834   0.05269  -0.0680   0.2773   0.6842
  13.750   1.4790   0.06574   0.06014  -0.0678   0.2709   0.6845
  14.000   1.4586   0.07083   0.06527  -0.0678   0.2656   0.6850
  14.250   1.4414   0.07560   0.07007  -0.0679   0.2607   0.6855
  14.500   1.4302   0.07973   0.07418  -0.0681   0.2555   0.6860
  14.750   1.4216   0.08373   0.07827  -0.0684   0.2516   0.6866
  15.000   1.4158   0.08737   0.08195  -0.0687   0.2458   0.6874
  15.250   1.4058   0.09151   0.08609  -0.0691   0.2384   0.6880
  15.500   1.3917   0.09627   0.09086  -0.0696   0.2263   0.6887
  15.750   1.3782   0.10089   0.09541  -0.0701   0.2155   0.6892
<< Back to WORTMANN FX 77-W-258 AIRFOIL (fx77w258-il)

Polar data table (+)

Polar graphs


<< Back to WORTMANN FX 77-W-258 AIRFOIL (fx77w258-il)