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WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il)
Reynolds number: 100,000
Max Cl/Cd: 17.5 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx77w153-il-100000.txt
Download as CSV file: xf-fx77w153-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3303   0.10441   0.09923  -0.0092   0.6278   0.1024
  -8.500  -0.3173   0.10153   0.09630  -0.0088   0.6204   0.1050
  -8.250  -0.3123   0.09840   0.09316  -0.0105   0.6146   0.1086
  -8.000  -0.3399   0.09388   0.08871  -0.0226   0.6136   0.1129
  -7.750  -0.3412   0.08941   0.08421  -0.0244   0.6097   0.1144
  -7.500  -0.3093   0.08715   0.08193  -0.0191   0.6018   0.1174
  -7.250  -0.3036   0.08406   0.07883  -0.0208   0.5971   0.1212
  -7.000  -0.3382   0.07894   0.07349  -0.0331   0.5973   0.1278
  -6.750  -0.3118   0.07572   0.07033  -0.0292   0.5917   0.1300
  -6.500  -0.2961   0.07323   0.06787  -0.0286   0.5866   0.1344
  -6.250  -0.3004   0.06883   0.06329  -0.0337   0.5841   0.1436
  -6.000  -0.2811   0.06643   0.06093  -0.0322   0.5799   0.1477
  -5.750  -0.2762   0.06301   0.05729  -0.0346   0.5775   0.1590
  -5.500  -0.2582   0.06072   0.05497  -0.0337   0.5745   0.1649
  -5.250  -0.2460   0.05773   0.05190  -0.0347   0.5716   0.1764
  -5.000  -0.2319   0.05524   0.04933  -0.0351   0.5687   0.1906
  -4.750  -0.2156   0.05310   0.04716  -0.0347   0.5658   0.2066
  -4.500  -0.1913   0.04020   0.03214  -0.0365   0.5652   0.0897
  -4.250  -0.1677   0.03768   0.02931  -0.0357   0.5626   0.0844
  -4.000  -0.1446   0.03483   0.02547  -0.0337   0.5605   0.0771
  -3.750  -0.1191   0.03321   0.02346  -0.0329   0.5584   0.0765
  -3.500  -0.0926   0.03144   0.02146  -0.0326   0.5559   0.0772
  -3.250  -0.0655   0.02996   0.01999  -0.0326   0.5528   0.0799
  -3.000  -0.0382   0.02917   0.01905  -0.0322   0.5495   0.0860
  -2.750  -0.0114   0.02829   0.01812  -0.0320   0.5466   0.0943
  -2.500   0.0153   0.02765   0.01741  -0.0317   0.5440   0.1044
  -2.250   0.0429   0.02712   0.01676  -0.0313   0.5417   0.1107
  -2.000   0.0698   0.02666   0.01644  -0.0313   0.5392   0.1180
  -1.750   0.0962   0.02645   0.01629  -0.0312   0.5363   0.1265
  -1.500   0.1204   0.02610   0.01611  -0.0307   0.5335   0.1376
  -1.250   0.1441   0.02575   0.01593  -0.0300   0.5310   0.1625
  -1.000   0.3092   0.02339   0.01603  -0.0531   0.5262   1.0000
  -0.750   0.3321   0.02389   0.01632  -0.0527   0.5245   1.0000
  -0.500   0.3556   0.02462   0.01703  -0.0530   0.5223   1.0000
  -0.250   0.3783   0.02542   0.01777  -0.0532   0.5200   1.0000
   0.000   0.4005   0.02623   0.01853  -0.0532   0.5176   1.0000
   0.250   0.4224   0.02695   0.01916  -0.0529   0.5148   1.0000
   0.500   0.4444   0.02750   0.01958  -0.0522   0.5121   1.0000
   0.750   0.4668   0.02797   0.01989  -0.0513   0.5098   1.0000
   1.000   0.4890   0.02862   0.02039  -0.0505   0.5078   1.0000
   1.250   0.5050   0.03045   0.02238  -0.0510   0.5036   1.0000
   1.500   0.5230   0.03162   0.02355  -0.0506   0.4993   1.0000
   1.750   0.5441   0.03217   0.02399  -0.0496   0.4958   1.0000
   2.000   0.5672   0.03248   0.02415  -0.0484   0.4932   1.0000
   2.250   0.5867   0.03353   0.02513  -0.0476   0.4907   1.0000
   2.500   0.5862   0.03716   0.02902  -0.0479   0.4853   1.0000
   2.750   0.5981   0.03886   0.03072  -0.0471   0.4811   1.0000
   3.000   0.6207   0.03923   0.03099  -0.0459   0.4781   1.0000
   3.250   0.6484   0.03910   0.03071  -0.0446   0.4760   1.0000
   3.500   0.4553   0.06104   0.05334  -0.0456   0.4959   1.0000
   3.750   0.4749   0.06267   0.05490  -0.0451   0.4938   1.0000
   4.000   0.4947   0.06461   0.05678  -0.0448   0.4926   1.0000
   4.250   0.5151   0.06685   0.05897  -0.0446   0.4914   1.0000
   4.500   0.5512   0.06279   0.05475  -0.0406   0.4602   1.0000
   4.750   0.5474   0.06629   0.05824  -0.0402   0.4597   1.0000
   5.000   0.5441   0.06970   0.06163  -0.0397   0.4573   1.0000
   5.250   0.5595   0.07236   0.06427  -0.0398   0.4581   1.0000
   5.500   0.4776   0.08156   0.07362  -0.0420   0.4785   1.0000
   5.750   0.5133   0.08354   0.07555  -0.0421   0.4760   1.0000
   6.000   0.4855   0.08589   0.07789  -0.0409   0.4652   1.0000
   6.250   0.5110   0.08766   0.07962  -0.0407   0.4612   1.0000
   6.500   0.5469   0.08991   0.08184  -0.0408   0.4592   1.0000
   6.750   0.5141   0.09224   0.08418  -0.0399   0.4483   1.0000
   7.000   0.5407   0.09409   0.08600  -0.0398   0.4445   1.0000
   7.500   0.5443   0.09864   0.09054  -0.0392   0.4310   1.0000
   7.750   0.5697   0.10071   0.09259  -0.0391   0.4280   1.0000
   8.000   0.6034   0.10337   0.09524  -0.0392   0.4264   1.0000
   8.250   0.5639   0.10590   0.09780  -0.0389   0.4170   1.0000
   8.500   0.5819   0.10799   0.09988  -0.0388   0.4132   1.0000
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