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WORTMANN FX 77-W-258 AIRFOIL (fx77w258-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 77-W-258 AIRFOIL (fx77w258-il)
Reynolds number: 50,000
Max Cl/Cd: 2.5 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx77w258-il-50000-n5.txt
Download as CSV file: xf-fx77w258-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.4090   0.12788   0.11962  -0.0297   0.6018   0.0759
 -14.250  -0.4662   0.11042   0.10203  -0.0401   0.6047   0.0753
 -14.000  -0.5351   0.09517   0.08645  -0.0491   0.6078   0.0746
 -13.750  -0.5755   0.08658   0.07755  -0.0532   0.6074   0.0744
 -13.500  -0.6018   0.08045   0.07112  -0.0554   0.6056   0.0745
 -13.250  -0.6191   0.07560   0.06598  -0.0567   0.6031   0.0749
 -13.000  -0.6305   0.07151   0.06155  -0.0573   0.6004   0.0754
 -12.750  -0.6329   0.06829   0.05805  -0.0575   0.5975   0.0761
 -12.250  -0.6071   0.06450   0.05407  -0.0576   0.5906   0.0782
 -12.000  -0.5953   0.06249   0.05191  -0.0576   0.5872   0.0796
 -11.750  -0.5842   0.06040   0.04959  -0.0576   0.5840   0.0814
 -11.500  -0.5649   0.05917   0.04832  -0.0574   0.5807   0.0833
 -11.250  -0.5467   0.05788   0.04694  -0.0573   0.5778   0.0857
 -11.000  -0.5281   0.05654   0.04538  -0.0570   0.5753   0.0885
 -10.750  -0.5057   0.05567   0.04447  -0.0567   0.5727   0.0914
 -10.500  -0.4820   0.05470   0.04338  -0.0567   0.5696   0.0951
 -10.250  -0.4573   0.05403   0.04276  -0.0566   0.5663   0.0990
 -10.000  -0.4355   0.05325   0.04193  -0.0564   0.5631   0.1041
  -9.750  -0.4159   0.05242   0.04106  -0.0561   0.5602   0.1103
  -9.500  -0.3978   0.05163   0.04031  -0.0556   0.5575   0.1165
  -9.250  -0.3804   0.05085   0.03955  -0.0551   0.5551   0.1233
  -9.000  -0.3625   0.05011   0.03879  -0.0545   0.5530   0.1312
  -8.750  -0.3435   0.04939   0.03814  -0.0543   0.5505   0.1411
  -8.500  -0.3267   0.04861   0.03750  -0.0540   0.5483   0.1527
  -8.250  -0.3126   0.04775   0.03684  -0.0535   0.5462   0.1656
  -8.000  -0.2998   0.04687   0.03612  -0.0529   0.5442   0.1824
  -7.750  -0.2893   0.04592   0.03535  -0.0521   0.5423   0.2029
  -7.500  -0.2813   0.04494   0.03465  -0.0511   0.5406   0.2280
  -7.250  -0.2749   0.04404   0.03403  -0.0497   0.5390   0.2632
  -7.000  -0.2690   0.04342   0.03375  -0.0479   0.5375   0.3095
  -6.750  -0.2502   0.04396   0.03478  -0.0457   0.5358   0.3689
  -6.500  -0.2103   0.04622   0.03728  -0.0440   0.5339   0.4234
  -6.250  -0.1830   0.04777   0.03880  -0.0424   0.5319   0.4597
  -6.000  -0.1659   0.04898   0.04001  -0.0412   0.5293   0.4886
  -5.750  -0.1525   0.05012   0.04113  -0.0394   0.5267   0.5135
  -5.500  -0.1412   0.05126   0.04222  -0.0374   0.5243   0.5359
  -5.000  -0.1167   0.05352   0.04432  -0.0335   0.5201   0.5758
  -4.750  -0.0884   0.05502   0.04569  -0.0323   0.5178   0.5904
  -4.500  -0.0706   0.05588   0.04641  -0.0307   0.5158   0.6059
  -4.250  -0.0579   0.05642   0.04681  -0.0287   0.5140   0.6214
  -4.000  -0.0518   0.05663   0.04687  -0.0265   0.5125   0.6375
  -3.750  -0.0241   0.05846   0.04871  -0.0265   0.5095   0.6451
  -3.500  -0.0318   0.05967   0.05000  -0.0242   0.5069   0.6592
  -3.250  -0.0133   0.06143   0.05177  -0.0236   0.5036   0.6667
  -3.000  -0.0240   0.06227   0.05261  -0.0206   0.5007   0.6801
  -2.750  -0.0007   0.06331   0.05357  -0.0199   0.4979   0.6870
  -2.250   0.0193   0.06403   0.05408  -0.0163   0.4939   0.7055
  -2.000   0.0384   0.06429   0.05421  -0.0152   0.4925   0.7133
  -1.750   0.0209   0.06541   0.05533  -0.0118   0.4904   0.7236
  -1.500  -0.0630   0.07126   0.06163  -0.0055   0.4842   0.7295
  -1.250  -0.0939   0.07307   0.06349  -0.0013   0.4815   0.7372
  -1.000  -0.1057   0.07390   0.06426   0.0009   0.4790   0.7455
  -0.750  -0.0959   0.07475   0.06504   0.0025   0.4766   0.7505
  -0.500  -0.0819   0.07523   0.06541   0.0036   0.4745   0.7564
  -0.250  -0.0660   0.07539   0.06542   0.0040   0.4728   0.7637
   0.000  -0.0441   0.07550   0.06540   0.0043   0.4714   0.7686
   0.250  -0.0705   0.07829   0.06826   0.0064   0.4683   0.7725
   0.500  -0.0787   0.08019   0.07016   0.0073   0.4662   0.7762
   0.750  -0.0786   0.08166   0.07160   0.0076   0.4635   0.7800
   1.000  -0.0709   0.08281   0.07268   0.0073   0.4606   0.7841
   1.250  -0.0560   0.08380   0.07356   0.0062   0.4579   0.7889
   1.500  -0.0413   0.08456   0.07426   0.0070   0.4556   0.7922
   1.750  -0.0225   0.08530   0.07492   0.0072   0.4537   0.7955
   2.000   0.0020   0.08590   0.07540   0.0069   0.4519   0.7985
   2.250   0.0079   0.08748   0.07693   0.0067   0.4488   0.8016
   2.500   0.0025   0.08959   0.07907   0.0063   0.4445   0.8044
   2.750   0.0120   0.09124   0.08068   0.0052   0.4420   0.8066
   3.000   0.0251   0.09284   0.08223   0.0040   0.4400   0.8085
   3.250   0.0406   0.09440   0.08373   0.0025   0.4380   0.8103
   3.500   0.0573   0.09579   0.08508   0.0016   0.4362   0.8119
   3.750   0.0764   0.09690   0.08613   0.0012   0.4341   0.8137
   4.000   0.1008   0.09786   0.08701   0.0007   0.4322   0.8159
   4.250   0.1305   0.09876   0.08782   0.0001   0.4306   0.8183
   4.500   0.1087   0.10161   0.09077   0.0000   0.4251   0.8205
   4.750   0.1168   0.10353   0.09269  -0.0008   0.4228   0.8229
   5.000   0.1282   0.10542   0.09457  -0.0018   0.4210   0.8250
   5.250   0.1418   0.10731   0.09644  -0.0030   0.4192   0.8268
   5.500   0.1570   0.10923   0.09834  -0.0044   0.4177   0.8282
   5.750   0.1753   0.11101   0.10009  -0.0059   0.4158   0.8297
   6.000   0.1998   0.11257   0.10160  -0.0074   0.4136   0.8315
   6.250   0.2313   0.11404   0.10301  -0.0091   0.4117   0.8333
   6.500   0.2225   0.11631   0.10533  -0.0094   0.4071   0.8345
   6.750   0.2287   0.11832   0.10736  -0.0103   0.4039   0.8357
   7.000   0.2416   0.12007   0.10912  -0.0113   0.4005   0.8368
   7.250   0.2602   0.12164   0.11068  -0.0123   0.3973   0.8380
   7.500   0.2837   0.12313   0.11214  -0.0135   0.3947   0.8393
   7.750   0.3122   0.12466   0.11363  -0.0147   0.3928   0.8407
   8.000   0.3052   0.12707   0.11610  -0.0157   0.3877   0.8417
   8.250   0.3144   0.12904   0.11810  -0.0169   0.3835   0.8430
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