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WORTMANN FX 80-080 (fx80080-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 80-080 (fx80080-il)
Reynolds number: 100,000
Max Cl/Cd: 57.32 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx80080-il-100000.txt
Download as CSV file: xf-fx80080-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 80-080                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4536   0.09295   0.08816  -0.0353   1.0000   0.0829
  -8.000  -0.4701   0.09044   0.08579  -0.0386   1.0000   0.0836
  -7.750  -0.4843   0.08739   0.08282  -0.0440   1.0000   0.0841
  -7.500  -0.4718   0.08234   0.07783  -0.0389   1.0000   0.0864
  -7.250  -0.4661   0.07959   0.07513  -0.0361   1.0000   0.0899
  -7.000  -0.4715   0.07656   0.07215  -0.0366   1.0000   0.0929
  -6.750  -0.4819   0.07380   0.06940  -0.0380   1.0000   0.0959
  -6.500  -0.5037   0.07290   0.06812  -0.0415   1.0000   0.0981
  -6.250  -0.4946   0.06743   0.06301  -0.0369   1.0000   0.1007
  -6.000  -0.4922   0.06499   0.06059  -0.0346   1.0000   0.1045
  -5.750  -0.4942   0.06191   0.05714  -0.0378   1.0000   0.1129
  -5.500  -0.4874   0.05853   0.05396  -0.0346   1.0000   0.1164
  -5.250  -0.4798   0.05542   0.05056  -0.0361   1.0000   0.1275
  -5.000  -0.4693   0.05284   0.04796  -0.0349   1.0000   0.1378
  -4.750  -0.4583   0.04984   0.04473  -0.0355   1.0000   0.1552
  -4.500  -0.4479   0.04701   0.04202  -0.0337   1.0000   0.1721
  -3.750  -0.3621   0.03409   0.02739  -0.0381   1.0000   0.1163
  -3.500  -0.3201   0.02847   0.02048  -0.0375   1.0000   0.0670
  -3.250  -0.2933   0.02599   0.01749  -0.0371   1.0000   0.0644
  -3.000  -0.2679   0.02442   0.01551  -0.0363   1.0000   0.0675
  -2.750  -0.2426   0.02318   0.01386  -0.0354   1.0000   0.0710
  -2.500  -0.2180   0.02138   0.01203  -0.0348   1.0000   0.0746
  -2.250  -0.1941   0.02039   0.01094  -0.0340   1.0000   0.0823
  -2.000  -0.1709   0.01951   0.01008  -0.0332   1.0000   0.0984
  -1.750  -0.1476   0.01839   0.00914  -0.0326   1.0000   0.1277
  -1.500  -0.1327   0.01536   0.00904  -0.0294   1.0000   0.7477
  -1.250  -0.1164   0.01481   0.00874  -0.0252   1.0000   1.0000
  -1.000  -0.0930   0.01501   0.00861  -0.0252   1.0000   1.0000
  -0.750  -0.0697   0.01525   0.00858  -0.0252   1.0000   1.0000
  -0.500  -0.0466   0.01552   0.00859  -0.0252   1.0000   1.0000
  -0.250  -0.0237   0.01582   0.00869  -0.0252   1.0000   1.0000
   0.000   0.0116   0.01633   0.00901  -0.0276   0.9963   1.0000
   0.250   0.0485   0.01682   0.00934  -0.0303   0.9907   1.0000
   0.500   0.0846   0.01732   0.00969  -0.0328   0.9850   1.0000
   0.750   0.1223   0.01786   0.01012  -0.0355   0.9791   1.0000
   1.000   0.1561   0.01831   0.01050  -0.0376   0.9726   1.0000
   1.250   0.1944   0.01885   0.01098  -0.0404   0.9663   1.0000
   1.500   0.2274   0.01928   0.01138  -0.0422   0.9585   1.0000
   1.750   0.2696   0.01983   0.01191  -0.0456   0.9517   1.0000
   2.000   0.3006   0.02020   0.01230  -0.0469   0.9424   1.0000
   2.250   0.3394   0.02067   0.01283  -0.0496   0.9346   1.0000
   2.500   0.3792   0.02104   0.01326  -0.0524   0.9252   1.0000
   2.750   0.4142   0.02135   0.01365  -0.0541   0.9139   1.0000
   3.000   0.4531   0.02161   0.01401  -0.0564   0.9025   1.0000
   3.250   0.4965   0.02169   0.01428  -0.0591   0.8899   1.0000
   3.500   0.5453   0.02144   0.01422  -0.0623   0.8749   1.0000
   3.750   0.6149   0.02023   0.01330  -0.0678   0.8570   1.0000
   4.000   0.6793   0.01862   0.01206  -0.0716   0.8355   1.0000
   4.250   0.7350   0.01693   0.01067  -0.0735   0.8118   1.0000
   4.500   0.7659   0.01590   0.00986  -0.0714   0.7791   1.0000
   4.750   0.7936   0.01484   0.00900  -0.0687   0.7308   1.0000
   5.000   0.8128   0.01418   0.00823  -0.0643   0.6125   1.0000
   5.250   0.8072   0.01657   0.00839  -0.0570   0.2742   1.0000
   5.500   0.8109   0.01905   0.00981  -0.0532   0.1612   1.0000
   5.750   0.8248   0.02081   0.01121  -0.0509   0.1204   1.0000
   6.000   0.8446   0.02252   0.01283  -0.0493   0.0975   1.0000
   6.250   0.8676   0.02461   0.01469  -0.0487   0.0804   1.0000
   6.500   0.8964   0.02660   0.01694  -0.0482   0.0714   1.0000
   6.750   0.9245   0.02912   0.01961  -0.0480   0.0631   1.0000
   7.000   0.9508   0.03151   0.02220  -0.0474   0.0572   1.0000
   7.250   0.9760   0.03601   0.02695  -0.0470   0.0541   1.0000
   7.500   0.9924   0.03791   0.02954  -0.0443   0.0502   1.0000
   7.750   1.0078   0.04168   0.03387  -0.0420   0.0496   1.0000
   8.000   1.0188   0.04610   0.03882  -0.0394   0.0507   1.0000
   8.250   1.0270   0.05099   0.04410  -0.0370   0.0525   1.0000
  10.750   0.7777   0.10688   0.10294  -0.0255   0.1338   1.0000
  11.000   0.7358   0.11418   0.11018  -0.0330   0.1334   1.0000
  11.250   0.7081   0.11997   0.11587  -0.0381   0.1326   1.0000
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