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WORTMANN FX 082-512 AIRFOIL (fx082512-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 082-512 AIRFOIL (fx082512-il)
Reynolds number: 50,000
Max Cl/Cd: 31.2 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx082512-il-50000.txt
Download as CSV file: xf-fx082512-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 082-512 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4087   0.11069   0.10313  -0.0221   1.0000   0.2947
  -8.250  -0.4852   0.09611   0.08884  -0.0317   1.0000   0.1931
  -8.000  -0.6296   0.07246   0.06587  -0.0474   1.0000   0.1585
  -7.750  -0.6494   0.06238   0.05576  -0.0553   1.0000   0.1564
  -7.500  -0.6505   0.04472   0.03719  -0.0798   1.0000   0.1549
  -7.250  -0.6267   0.04052   0.03268  -0.0836   1.0000   0.1628
  -7.000  -0.5956   0.03654   0.02821  -0.0885   1.0000   0.1728
  -6.750  -0.5761   0.03563   0.02749  -0.0868   1.0000   0.1829
  -6.500  -0.5533   0.03459   0.02652  -0.0863   1.0000   0.1936
  -6.250  -0.5301   0.03403   0.02607  -0.0855   1.0000   0.2061
  -6.000  -0.5076   0.03387   0.02601  -0.0842   1.0000   0.2184
  -5.750  -0.4903   0.03498   0.02728  -0.0807   1.0000   0.2324
  -5.500  -0.4733   0.03624   0.02861  -0.0770   1.0000   0.2468
  -5.250  -0.4478   0.03650   0.02875  -0.0764   1.0000   0.2712
  -5.000  -0.4288   0.03806   0.03028  -0.0732   1.0000   0.3007
  -4.750  -0.4161   0.04026   0.03246  -0.0678   1.0000   0.3319
  -4.500  -0.4066   0.04229   0.03445  -0.0615   1.0000   0.3628
  -4.250  -0.3991   0.04391   0.03600  -0.0550   1.0000   0.3882
  -4.000  -0.3920   0.04505   0.03709  -0.0488   1.0000   0.4102
  -3.750  -0.3799   0.04589   0.03780  -0.0447   1.0000   0.4381
  -3.500  -0.3811   0.04692   0.03890  -0.0359   1.0000   0.4571
  -3.250  -0.3772   0.04752   0.03946  -0.0292   1.0000   0.4796
  -3.000  -0.3604   0.04726   0.03905  -0.0280   1.0000   0.5017
  -2.750  -0.3492   0.04699   0.03871  -0.0246   1.0000   0.5179
  -2.500  -0.3325   0.04651   0.03813  -0.0234   1.0000   0.5330
  -2.250  -0.3233   0.04606   0.03764  -0.0195   1.0000   0.5446
  -2.000  -0.3093   0.04561   0.03712  -0.0175   1.0000   0.5613
  -1.750  -0.2966   0.04508   0.03655  -0.0150   1.0000   0.5756
  -1.500  -0.2816   0.04446   0.03588  -0.0135   1.0000   0.5880
  -1.250  -0.2645   0.04385   0.03522  -0.0126   1.0000   0.6015
  -1.000  -0.2429   0.04326   0.03455  -0.0132   1.0000   0.6141
  -0.750  -0.2231   0.04262   0.03386  -0.0133   1.0000   0.6218
  -0.500  -0.1909   0.04190   0.03305  -0.0172   1.0000   0.6226
  -0.250  -0.1523   0.04113   0.03214  -0.0230   1.0000   0.6168
   0.000  -0.1046   0.04055   0.03139  -0.0313   1.0000   0.6099
   0.250  -0.0728   0.04005   0.03085  -0.0348   1.0000   0.6081
   0.500  -0.0396   0.03969   0.03042  -0.0386   1.0000   0.6069
   0.750  -0.0061   0.03942   0.03012  -0.0425   1.0000   0.6057
   1.000   0.0279   0.03925   0.02991  -0.0465   1.0000   0.6042
   1.250   0.0614   0.03919   0.02983  -0.0504   1.0000   0.6032
   1.500   0.0924   0.03924   0.02988  -0.0535   1.0000   0.6040
   1.750   0.1227   0.03941   0.03005  -0.0565   1.0000   0.6054
   2.000   0.1528   0.03967   0.03034  -0.0596   1.0000   0.6069
   2.250   0.1827   0.04003   0.03073  -0.0626   1.0000   0.6080
   2.500   0.2122   0.04049   0.03123  -0.0655   1.0000   0.6090
   2.750   0.2416   0.04108   0.03188  -0.0686   1.0000   0.6110
   3.000   0.2647   0.04168   0.03259  -0.0700   1.0000   0.6138
   3.250   0.2876   0.04241   0.03344  -0.0715   1.0000   0.6169
   3.500   0.3114   0.04329   0.03443  -0.0734   1.0000   0.6202
   3.750   0.4119   0.04535   0.03667  -0.0885   0.9618   0.6270
   4.000   0.5179   0.04507   0.03674  -0.1009   0.9126   0.6365
   4.250   0.5912   0.04437   0.03633  -0.1080   0.8826   0.6457
   4.500   0.6577   0.04262   0.03494  -0.1124   0.8479   0.6546
   4.750   0.7301   0.04025   0.03300  -0.1168   0.8201   0.6641
   5.000   0.8157   0.03468   0.02806  -0.1186   0.7741   0.6787
   5.250   0.8706   0.02937   0.02322  -0.1144   0.6923   0.6920
   5.500   0.9058   0.02903   0.02026  -0.1087   0.2969   0.7030
   5.750   0.9195   0.03104   0.02167  -0.1067   0.2439   0.7115
   6.000   0.9457   0.03257   0.02293  -0.1064   0.2139   0.7235
   6.250   0.9888   0.03399   0.02429  -0.1083   0.1901   0.7412
   6.500   1.0602   0.03629   0.02635  -0.1146   0.1649   0.7701
   6.750   1.1119   0.03878   0.02894  -0.1177   0.1502   0.8033
   7.000   1.1415   0.04067   0.03127  -0.1169   0.1424   0.8502
   7.250   1.1806   0.04388   0.03476  -0.1190   0.1350   1.0000
   7.500   1.2229   0.04806   0.03937  -0.1220   0.1311   1.0000
   7.750   1.2495   0.05196   0.04360  -0.1219   0.1287   1.0000
   8.000   1.2698   0.05586   0.04778  -0.1208   0.1263   1.0000
   8.250   1.2784   0.05997   0.05251  -0.1177   0.1285   1.0000
   8.500   1.2831   0.06469   0.05777  -0.1146   0.1327   1.0000
   8.750   1.2936   0.07001   0.06335  -0.1128   0.1362   1.0000
   9.000   1.2727   0.07437   0.06854  -0.1073   0.1439   1.0000
   9.250   1.2677   0.08012   0.07458  -0.1048   0.1497   1.0000
   9.500   1.2282   0.08525   0.08026  -0.1000   0.1588   1.0000
  10.000   1.0881   0.09421   0.08997  -0.0837   0.1667   1.0000
  10.250   1.0229   0.10075   0.09670  -0.0830   0.1661   1.0000
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