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=200,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 77-W-258 AIRFOIL (fx77w258-il)
Reynolds number: 200,000
Max Cl/Cd: 36.54 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx77w258-il-200000-n5.txt
Download as CSV file: xf-fx77w258-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.500  -0.7637   0.14021   0.13420  -0.0052   0.5760   0.0202
 -19.250  -0.7839   0.13188   0.12568  -0.0103   0.5729   0.0202
 -19.000  -0.8005   0.12448   0.11809  -0.0147   0.5687   0.0202
 -18.750  -0.8145   0.11771   0.11115  -0.0186   0.5638   0.0202
 -18.500  -0.8264   0.11152   0.10478  -0.0221   0.5585   0.0202
 -18.250  -0.8363   0.10581   0.09889  -0.0252   0.5535   0.0202
 -18.000  -0.8445   0.10049   0.09342  -0.0280   0.5485   0.0203
 -17.750  -0.8511   0.09554   0.08832  -0.0305   0.5432   0.0203
 -17.500  -0.8563   0.09093   0.08355  -0.0327   0.5380   0.0204
 -17.000  -0.8616   0.08276   0.07507  -0.0364   0.5293   0.0206
 -16.750  -0.8623   0.07906   0.07123  -0.0380   0.5254   0.0207
 -16.500  -0.8618   0.07564   0.06766  -0.0393   0.5217   0.0208
 -16.250  -0.8602   0.07244   0.06433  -0.0405   0.5182   0.0209
 -16.000  -0.8570   0.06952   0.06126  -0.0415   0.5149   0.0211
 -15.500  -0.8489   0.06406   0.05556  -0.0431   0.5093   0.0213
 -15.250  -0.8436   0.06158   0.05300  -0.0437   0.5065   0.0215
 -15.000  -0.8374   0.05925   0.05058  -0.0442   0.5038   0.0217
 -14.750  -0.8301   0.05711   0.04836  -0.0445   0.5012   0.0218
 -14.500  -0.8223   0.05509   0.04625  -0.0448   0.4986   0.0221
 -14.250  -0.8132   0.05325   0.04431  -0.0450   0.4963   0.0223
 -14.000  -0.8037   0.05149   0.04246  -0.0451   0.4940   0.0225
 -13.750  -0.7931   0.04989   0.04075  -0.0452   0.4919   0.0228
 -13.500  -0.7820   0.04835   0.03914  -0.0452   0.4901   0.0231
 -13.250  -0.7706   0.04687   0.03761  -0.0451   0.4882   0.0233
 -13.000  -0.7583   0.04552   0.03620  -0.0449   0.4863   0.0236
 -12.750  -0.7458   0.04423   0.03484  -0.0447   0.4843   0.0239
 -12.500  -0.7330   0.04299   0.03355  -0.0445   0.4823   0.0243
 -12.250  -0.7195   0.04183   0.03236  -0.0442   0.4802   0.0246
 -12.000  -0.7050   0.04077   0.03124  -0.0440   0.4782   0.0250
 -11.750  -0.6902   0.03974   0.03016  -0.0437   0.4763   0.0255
 -11.500  -0.6753   0.03875   0.02910  -0.0434   0.4745   0.0260
 -11.250  -0.6597   0.03782   0.02811  -0.0431   0.4728   0.0267
 -10.750  -0.6267   0.03613   0.02630  -0.0425   0.4701   0.0285
 -10.500  -0.6099   0.03530   0.02542  -0.0421   0.4688   0.0296
 -10.250  -0.5930   0.03448   0.02455  -0.0418   0.4675   0.0306
 -10.000  -0.5759   0.03368   0.02371  -0.0414   0.4661   0.0314
  -9.750  -0.5586   0.03291   0.02289  -0.0410   0.4648   0.0324
  -9.500  -0.5409   0.03218   0.02210  -0.0406   0.4635   0.0335
  -9.250  -0.5225   0.03150   0.02135  -0.0403   0.4622   0.0345
  -9.000  -0.5053   0.03074   0.02056  -0.0398   0.4609   0.0355
  -8.750  -0.4873   0.03005   0.01982  -0.0394   0.4597   0.0366
  -8.500  -0.4686   0.02941   0.01911  -0.0390   0.4585   0.0380
  -8.250  -0.4515   0.02866   0.01835  -0.0385   0.4574   0.0394
  -8.000  -0.4341   0.02796   0.01761  -0.0380   0.4563   0.0410
  -7.750  -0.4169   0.02730   0.01692  -0.0375   0.4553   0.0427
  -7.500  -0.4021   0.02664   0.01626  -0.0365   0.4543   0.0447
  -7.250  -0.3883   0.02606   0.01568  -0.0354   0.4533   0.0470
  -7.000  -0.3749   0.02552   0.01516  -0.0343   0.4524   0.0499
  -6.750  -0.3568   0.02502   0.01467  -0.0339   0.4514   0.0549
  -6.500  -0.3355   0.02464   0.01424  -0.0338   0.4504   0.0616
  -6.250  -0.3134   0.02422   0.01380  -0.0338   0.4497   0.0668
  -6.000  -0.2914   0.02376   0.01337  -0.0339   0.4489   0.0723
  -5.750  -0.2694   0.02327   0.01297  -0.0340   0.4480   0.0799
  -5.500  -0.2459   0.02285   0.01264  -0.0342   0.4471   0.0982
  -5.250  -0.2214   0.02243   0.01229  -0.0345   0.4457   0.1122
  -5.000  -0.1972   0.02189   0.01191  -0.0349   0.4440   0.1422
  -4.750  -0.1717   0.02137   0.01153  -0.0355   0.4422   0.1660
  -4.500  -0.1451   0.02089   0.01118  -0.0362   0.4406   0.2046
  -4.250  -0.1179   0.02030   0.01080  -0.0373   0.4391   0.2530
  -4.000  -0.0896   0.01966   0.01041  -0.0386   0.4378   0.3128
  -3.750  -0.0603   0.01893   0.01006  -0.0401   0.4366   0.3896
  -3.500  -0.0308   0.01860   0.01011  -0.0410   0.4356   0.4658
  -3.250  -0.0023   0.01890   0.01069  -0.0408   0.4346   0.5187
  -3.000   0.0271   0.01935   0.01120  -0.0407   0.4336   0.5563
  -2.750   0.0573   0.01975   0.01159  -0.0409   0.4327   0.5757
  -2.500   0.0871   0.02026   0.01207  -0.0410   0.4317   0.5885
  -2.250   0.1187   0.02065   0.01235  -0.0418   0.4306   0.6026
  -2.000   0.1520   0.02080   0.01239  -0.0434   0.4298   0.6171
  -1.750   0.1805   0.02133   0.01297  -0.0431   0.4289   0.6233
  -1.500   0.2110   0.02165   0.01328  -0.0437   0.4279   0.6311
  -1.250   0.2429   0.02181   0.01337  -0.0449   0.4268   0.6372
  -1.000   0.2711   0.02218   0.01378  -0.0448   0.4257   0.6400
  -0.750   0.2995   0.02256   0.01418  -0.0448   0.4245   0.6432
  -0.500   0.3281   0.02294   0.01457  -0.0450   0.4233   0.6479
  -0.250   0.3591   0.02322   0.01481  -0.0459   0.4221   0.6551
   0.000   0.3872   0.02360   0.01519  -0.0459   0.4210   0.6597
   0.250   0.4138   0.02403   0.01567  -0.0454   0.4198   0.6632
   0.500   0.4415   0.02438   0.01603  -0.0453   0.4187   0.6672
   0.750   0.4709   0.02462   0.01624  -0.0458   0.4177   0.6712
   1.000   0.5017   0.02474   0.01631  -0.0469   0.4166   0.6745
   1.250   0.5335   0.02482   0.01631  -0.0483   0.4157   0.6771
   1.500   0.5640   0.02492   0.01635  -0.0492   0.4147   0.6790
   1.750   0.5928   0.02505   0.01646  -0.0496   0.4138   0.6802
   2.000   0.6219   0.02521   0.01659  -0.0501   0.4130   0.6814
   2.250   0.6513   0.02540   0.01673  -0.0508   0.4121   0.6825
   2.500   0.6805   0.02566   0.01696  -0.0515   0.4112   0.6836
   2.750   0.7074   0.02597   0.01734  -0.0519   0.4100   0.6847
   3.000   0.7334   0.02629   0.01775  -0.0523   0.4082   0.6860
   3.250   0.7595   0.02660   0.01813  -0.0527   0.4062   0.6873
   3.500   0.7858   0.02690   0.01848  -0.0532   0.4043   0.6888
   3.750   0.8127   0.02718   0.01879  -0.0537   0.4026   0.6903
   4.000   0.8398   0.02744   0.01906  -0.0542   0.4011   0.6919
   4.250   0.8671   0.02770   0.01933  -0.0548   0.3997   0.6936
   4.500   0.8945   0.02798   0.01960  -0.0554   0.3986   0.6957
   4.750   0.9225   0.02823   0.01984  -0.0561   0.3975   0.6977
   5.000   0.9508   0.02844   0.02004  -0.0569   0.3965   0.6989
   5.250   0.9793   0.02864   0.02021  -0.0577   0.3955   0.6998
   5.500   1.0068   0.02880   0.02037  -0.0581   0.3947   0.7007
   5.750   1.0345   0.02899   0.02054  -0.0586   0.3938   0.7015
   6.000   1.0623   0.02920   0.02074  -0.0591   0.3929   0.7023
   6.250   1.0853   0.02970   0.02129  -0.0592   0.3917   0.7032
   6.500   1.0912   0.03107   0.02289  -0.0576   0.3894   0.7041
   6.750   1.0917   0.03270   0.02472  -0.0556   0.3868   0.7051
   7.000   1.0819   0.03466   0.02687  -0.0526   0.3840   0.7060
   7.250   1.0443   0.03832   0.03072  -0.0485   0.3804   0.7071
   7.500   1.0410   0.04078   0.03326  -0.0482   0.3781   0.7081
   7.750   1.0599   0.04151   0.03400  -0.0485   0.3769   0.7091
   8.000   1.0859   0.04163   0.03411  -0.0489   0.3761   0.7100
   8.250   1.1150   0.04149   0.03395  -0.0493   0.3754   0.7110
   8.500   1.1452   0.04128   0.03372  -0.0497   0.3748   0.7120
   8.750   1.1763   0.04103   0.03343  -0.0502   0.3741   0.7130
   9.750   0.7670   0.10028   0.09349  -0.0539   0.3116   0.7138
  10.000   0.7841   0.10139   0.09461  -0.0543   0.3099   0.7146
<< 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)