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WORTMANN FX 08-S-176 AIRFOIL (fx08s176-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 08-S-176 AIRFOIL (fx08s176-il)
Reynolds number: 1,000,000
Max Cl/Cd: 142.02 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx08s176-il-1000000.txt
Download as CSV file: xf-fx08s176-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 08-S-176 AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.0586   0.08835   0.08473  -0.0959   0.5728   0.0131
 -10.250  -0.0657   0.08179   0.07822  -0.0996   0.5723   0.0142
 -10.000  -0.0656   0.07792   0.07436  -0.1014   0.5716   0.0142
  -9.750  -0.0695   0.07321   0.06967  -0.1039   0.5709   0.0142
  -9.500  -0.0783   0.06739   0.06389  -0.1076   0.5701   0.0143
  -9.250  -0.3732   0.02749   0.02290  -0.0980   0.5723   0.0101
  -9.000  -0.3698   0.02469   0.01970  -0.0952   0.5714   0.0105
  -8.750  -0.3526   0.02370   0.01851  -0.0940   0.5703   0.0107
  -8.500  -0.3487   0.02047   0.01484  -0.0913   0.5693   0.0113
  -8.250  -0.3268   0.01988   0.01419  -0.0907   0.5688   0.0115
  -8.000  -0.3028   0.01962   0.01391  -0.0903   0.5682   0.0119
  -7.750  -0.2790   0.01927   0.01350  -0.0899   0.5676   0.0123
  -7.500  -0.2551   0.01880   0.01295  -0.0895   0.5669   0.0128
  -7.250  -0.2315   0.01816   0.01220  -0.0890   0.5661   0.0134
  -7.000  -0.2064   0.01780   0.01174  -0.0887   0.5652   0.0139
  -6.750  -0.1803   0.01774   0.01160  -0.0885   0.5642   0.0143
  -6.500  -0.1598   0.01581   0.00949  -0.0877   0.5633   0.0152
  -6.250  -0.1342   0.01549   0.00915  -0.0876   0.5624   0.0158
  -6.000  -0.1082   0.01516   0.00876  -0.0874   0.5615   0.0165
  -5.750  -0.0822   0.01474   0.00829  -0.0873   0.5606   0.0172
  -5.500  -0.0559   0.01439   0.00787  -0.0871   0.5598   0.0179
  -5.250  -0.0288   0.01427   0.00770  -0.0872   0.5590   0.0185
  -5.000  -0.0041   0.01351   0.00684  -0.0868   0.5582   0.0193
  -4.750   0.0201   0.01285   0.00614  -0.0863   0.5573   0.0202
  -4.500   0.0460   0.01256   0.00582  -0.0862   0.5563   0.0210
  -4.250   0.0724   0.01241   0.00564  -0.0861   0.5549   0.0219
  -4.000   0.0990   0.01219   0.00540  -0.0861   0.5542   0.0229
  -3.750   0.1255   0.01191   0.00510  -0.0860   0.5536   0.0237
  -3.500   0.1522   0.01168   0.00486  -0.0859   0.5529   0.0243
  -3.250   0.1787   0.01141   0.00455  -0.0859   0.5521   0.0249
  -3.000   0.2047   0.01106   0.00417  -0.0857   0.5513   0.0268
  -2.750   0.2320   0.01089   0.00399  -0.0858   0.5505   0.0287
  -2.500   0.2597   0.01075   0.00384  -0.0860   0.5496   0.0304
  -2.250   0.2875   0.01063   0.00370  -0.0861   0.5486   0.0321
  -2.000   0.3152   0.01045   0.00355  -0.0863   0.5477   0.0405
  -1.750   0.3430   0.01029   0.00348  -0.0865   0.5466   0.0651
  -1.500   0.3711   0.01017   0.00339  -0.0868   0.5456   0.0802
  -1.250   0.3990   0.01000   0.00331  -0.0871   0.5447   0.1109
  -1.000   0.4249   0.00941   0.00320  -0.0875   0.5435   0.2807
  -0.750   0.4503   0.00809   0.00304  -0.0884   0.5422   0.6592
  -0.500   0.4767   0.00797   0.00333  -0.0882   0.5403   0.7925
  -0.250   0.5046   0.00807   0.00347  -0.0882   0.5394   0.8217
   0.000   0.5322   0.00821   0.00362  -0.0881   0.5385   0.8373
   0.250   0.5606   0.00833   0.00372  -0.0882   0.5373   0.8468
   0.500   0.5870   0.00842   0.00383  -0.0879   0.5359   0.8521
   0.750   0.6148   0.00852   0.00391  -0.0879   0.5343   0.8585
   1.000   0.6424   0.00858   0.00395  -0.0880   0.5329   0.8630
   1.250   0.6679   0.00869   0.00406  -0.0874   0.5316   0.8676
   1.500   0.6954   0.00878   0.00413  -0.0874   0.5304   0.8720
   1.750   0.7249   0.00883   0.00416  -0.0881   0.5293   0.8745
   2.000   0.7542   0.00889   0.00418  -0.0887   0.5281   0.8763
   2.250   0.7799   0.00900   0.00428  -0.0883   0.5267   0.8791
   2.500   0.8062   0.00911   0.00440  -0.0882   0.5255   0.8819
   2.750   0.8343   0.00913   0.00444  -0.0885   0.5245   0.8836
   3.000   0.8629   0.00915   0.00447  -0.0890   0.5234   0.8852
   3.250   0.8916   0.00917   0.00451  -0.0895   0.5220   0.8871
   3.500   0.9208   0.00921   0.00455  -0.0901   0.5206   0.8887
   3.750   0.9503   0.00923   0.00458  -0.0909   0.5192   0.8899
   4.000   0.9787   0.00922   0.00457  -0.0913   0.5176   0.8913
   4.250   1.0060   0.00920   0.00456  -0.0915   0.5161   0.8926
   4.500   1.0337   0.00922   0.00458  -0.0918   0.5145   0.8938
   4.750   1.0616   0.00930   0.00465  -0.0922   0.5126   0.8949
   5.000   1.0891   0.00934   0.00473  -0.0925   0.5110   0.8961
   5.250   1.1167   0.00936   0.00480  -0.0929   0.5095   0.8975
   5.500   1.1445   0.00938   0.00486  -0.0933   0.5076   0.8989
   5.750   1.1726   0.00939   0.00490  -0.0937   0.5053   0.9003
   6.000   1.2006   0.00934   0.00487  -0.0942   0.5019   0.9014
   6.250   1.2281   0.00935   0.00486  -0.0946   0.4973   0.9025
   6.500   1.2561   0.00931   0.00488  -0.0950   0.4918   0.9037
   6.750   1.2831   0.00934   0.00489  -0.0954   0.4857   0.9047
   7.000   1.3095   0.00933   0.00493  -0.0955   0.4780   0.9060
   7.250   1.3336   0.00939   0.00498  -0.0952   0.4684   0.9073
   7.500   1.3551   0.00957   0.00512  -0.0945   0.4481   0.9088
   7.750   1.3709   0.01004   0.00545  -0.0929   0.4182   0.9105
   8.000   1.3777   0.01092   0.00612  -0.0898   0.3779   0.9122
   8.250   1.3768   0.01202   0.00700  -0.0855   0.3391   0.9142
   8.500   1.3662   0.01311   0.00792  -0.0795   0.3060   0.9168
   8.750   1.3461   0.01459   0.00923  -0.0724   0.2715   0.9197
   9.000   1.3124   0.01688   0.01142  -0.0648   0.2389   0.9237
   9.250   1.2891   0.01988   0.01442  -0.0607   0.2201   0.9273
   9.500   1.2596   0.02403   0.01852  -0.0572   0.1970   0.9307
   9.750   1.2264   0.02841   0.02280  -0.0535   0.1697   0.9334
  10.000   1.2052   0.03176   0.02609  -0.0505   0.1485   0.9362
  10.250   1.1826   0.03527   0.02952  -0.0476   0.1228   0.9391
  10.500   1.1583   0.03910   0.03321  -0.0449   0.0900   0.9419
  10.750   1.1312   0.04361   0.03752  -0.0426   0.0457   0.9442
  11.000   1.1256   0.04655   0.04038  -0.0417   0.0254   0.9459
  11.250   1.1214   0.04942   0.04322  -0.0408   0.0098   0.9479
  11.500   1.1275   0.05137   0.04523  -0.0404   0.0085   0.9502
  11.750   1.1353   0.05316   0.04708  -0.0401   0.0078   0.9526
  12.000   1.1429   0.05504   0.04902  -0.0399   0.0076   0.9556
  12.250   1.1491   0.05711   0.05116  -0.0397   0.0071   0.9589
  12.500   1.1572   0.05907   0.05318  -0.0397   0.0068   0.9644
  12.750   1.1624   0.06161   0.05580  -0.0400   0.0064   0.9713
  13.000   1.1695   0.06410   0.05836  -0.0407   0.0062   0.9926
  13.250   1.1727   0.06677   0.06110  -0.0408   0.0060   1.0000
  13.500   1.1732   0.06986   0.06426  -0.0410   0.0058   1.0000
  13.750   1.1760   0.07273   0.06720  -0.0413   0.0057   1.0000
  14.000   1.1824   0.07523   0.06975  -0.0417   0.0056   1.0000
  14.250   1.1878   0.07787   0.07245  -0.0421   0.0055   1.0000
  14.500   1.1916   0.08073   0.07537  -0.0426   0.0054   1.0000
  14.750   1.1947   0.08373   0.07843  -0.0431   0.0053   1.0000
  15.000   1.1978   0.08676   0.08153  -0.0437   0.0051   1.0000
  15.250   1.1996   0.09002   0.08486  -0.0443   0.0050   1.0000
  15.500   1.2024   0.09315   0.08805  -0.0450   0.0049   1.0000
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