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=100,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 77-W-258 AIRFOIL (fx77w258-il)
Reynolds number: 100,000
Max Cl/Cd: 1.21 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx77w258-il-100000.txt
Download as CSV file: xf-fx77w258-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.6053   0.09281   0.08645  -0.0507   0.6248   0.0756
 -14.250  -0.6329   0.08617   0.07963  -0.0536   0.6236   0.0750
 -14.000  -0.6652   0.07971   0.07293  -0.0558   0.6226   0.0742
 -13.750  -0.7005   0.07364   0.06656  -0.0572   0.6218   0.0733
 -13.500  -0.7304   0.06857   0.06116  -0.0577   0.6205   0.0728
 -13.250  -0.7469   0.06489   0.05719  -0.0575   0.6184   0.0729
 -13.000  -0.7576   0.06181   0.05383  -0.0571   0.6162   0.0732
 -12.750  -0.7645   0.05904   0.05079  -0.0565   0.6138   0.0736
 -12.500  -0.7680   0.05645   0.04798  -0.0558   0.6109   0.0741
 -12.250  -0.7687   0.05411   0.04539  -0.0549   0.6078   0.0746
 -12.000  -0.7701   0.05216   0.04317  -0.0534   0.6049   0.0751
 -11.750  -0.7705   0.05041   0.04108  -0.0517   0.6022   0.0757
 -11.500  -0.7441   0.04912   0.03981  -0.0519   0.5988   0.0771
 -11.250  -0.7217   0.04802   0.03864  -0.0518   0.5961   0.0784
 -11.000  -0.7040   0.04680   0.03725  -0.0513   0.5939   0.0796
 -10.750  -0.6851   0.04543   0.03572  -0.0510   0.5916   0.0809
 -10.500  -0.6617   0.04417   0.03432  -0.0510   0.5891   0.0821
 -10.250  -0.6277   0.04329   0.03357  -0.0519   0.5864   0.0839
 -10.000  -0.6005   0.04243   0.03267  -0.0521   0.5840   0.0862
  -9.750  -0.5744   0.04157   0.03170  -0.0521   0.5818   0.0887
  -9.500  -0.5446   0.04094   0.03116  -0.0525   0.5796   0.0921
  -9.250  -0.5181   0.04026   0.03040  -0.0525   0.5778   0.0959
  -9.000  -0.4895   0.03973   0.02987  -0.0526   0.5760   0.1006
  -8.750  -0.4572   0.03931   0.02956  -0.0527   0.5743   0.1060
  -8.500  -0.4280   0.03899   0.02937  -0.0527   0.5727   0.1122
  -8.250  -0.4020   0.03867   0.02923  -0.0527   0.5706   0.1191
  -8.000  -0.3800   0.03840   0.02911  -0.0524   0.5684   0.1269
  -7.750  -0.3608   0.03814   0.02901  -0.0519   0.5667   0.1368
  -7.500  -0.3449   0.03780   0.02890  -0.0510   0.5651   0.1502
  -7.250  -0.3340   0.03738   0.02874  -0.0496   0.5634   0.1671
  -7.000  -0.3289   0.03688   0.02848  -0.0476   0.5616   0.1920
  -6.750  -0.3321   0.03615   0.02814  -0.0448   0.5601   0.2244
  -6.500  -0.3366   0.03509   0.02756  -0.0427   0.5588   0.2821
  -6.250  -0.3382   0.03424   0.02742  -0.0405   0.5577   0.3772
  -6.000  -0.3057   0.03712   0.03109  -0.0360   0.5560   0.4866
  -5.750  -0.2698   0.03964   0.03357  -0.0340   0.5541   0.5262
  -5.500  -0.2569   0.04034   0.03413  -0.0337   0.5526   0.5589
  -5.250  -0.2374   0.04233   0.03616  -0.0338   0.5506   0.5783
  -5.000  -0.2074   0.04589   0.03979  -0.0330   0.5484   0.5858
  -4.750  -0.1932   0.04826   0.04218  -0.0327   0.5474   0.6012
  -4.500  -0.1871   0.05056   0.04450  -0.0326   0.5469   0.6177
  -4.250  -0.1722   0.05445   0.04847  -0.0312   0.5469   0.6231
  -4.000  -0.1782   0.05677   0.05079  -0.0306   0.5487   0.6381
  -3.750  -0.2095   0.06337   0.05762  -0.0309   0.5725   0.6413
  -3.500  -0.3800   0.06725   0.06192  -0.0313   0.6278   0.6377
  -3.250  -0.3673   0.06939   0.06403  -0.0267   0.6217   0.6450
  -3.000  -0.3406   0.07148   0.06600  -0.0254   0.6185   0.6600
  -2.750  -0.3141   0.07445   0.06891  -0.0218   0.6166   0.6698
  -2.500  -0.3362   0.07419   0.06861  -0.0194   0.6037   0.6801
  -2.250  -0.3204   0.07613   0.07052  -0.0146   0.5992   0.6880
  -2.000  -0.2911   0.07802   0.07228  -0.0135   0.5966   0.7028
  -1.750  -0.3089   0.07886   0.07313  -0.0085   0.5875   0.7084
  -1.500  -0.2921   0.07973   0.07389  -0.0082   0.5807   0.7229
  -1.250  -0.2762   0.08120   0.07533  -0.0033   0.5775   0.7307
  -1.000  -0.2451   0.08296   0.07695  -0.0032   0.5754   0.7460
  -0.750  -0.2725   0.08315   0.07719   0.0020   0.5662   0.7508
  -0.500  -0.2596   0.08407   0.07803   0.0037   0.5605   0.7635
  -0.250  -0.2446   0.08499   0.07889   0.0071   0.5574   0.7736
   0.000  -0.2174   0.08656   0.08035   0.0073   0.5554   0.7870
   0.250  -0.1944   0.08814   0.08187   0.0105   0.5541   0.7972
   0.500  -0.1583   0.09083   0.08444   0.0092   0.5532   0.8114
   0.750  -0.2126   0.08831   0.08199   0.0138   0.5388   0.8129
   1.000  -0.1965   0.08911   0.08274   0.0172   0.5362   0.8225
   1.250  -0.1621   0.09101   0.08451   0.0152   0.5343   0.8330
   1.500  -0.1345   0.09259   0.08602   0.0169   0.5332   0.8390
   1.750  -0.1782   0.09126   0.08475   0.0202   0.5204   0.8415
   2.000  -0.1549   0.09227   0.08567   0.0195   0.5171   0.8453
   2.250  -0.1241   0.09374   0.08705   0.0176   0.5149   0.8477
   2.500  -0.0878   0.09583   0.08903   0.0152   0.5134   0.8497
   2.750  -0.0471   0.09866   0.09176   0.0122   0.5124   0.8517
   3.000  -0.0940   0.09740   0.09058   0.0139   0.5003   0.8535
   3.250  -0.0712   0.09860   0.09172   0.0128   0.4970   0.8559
   3.500  -0.0473   0.09989   0.09295   0.0126   0.4948   0.8584
   3.750  -0.0186   0.10176   0.09476   0.0117   0.4933   0.8612
   4.000   0.0171   0.10443   0.09735   0.0098   0.4923   0.8633
   4.250   0.0590   0.10803   0.10087   0.0072   0.4915   0.8646
   4.500  -0.0011   0.10524   0.09819   0.0095   0.4783   0.8650
   4.750   0.0265   0.10693   0.09983   0.0077   0.4754   0.8660
   5.000   0.0595   0.10913   0.10196   0.0055   0.4734   0.8669
   5.250   0.0979   0.11207   0.10484   0.0029   0.4722   0.8679
   5.500   0.1404   0.11588   0.10859   0.0000   0.4713   0.8689
   5.750   0.0841   0.11370   0.10652   0.0017   0.4594   0.8692
   6.000   0.1091   0.11547   0.10825  -0.0001   0.4561   0.8700
<< 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)