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WORTMANN FX 082-512 AIRFOIL (fx082512-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 082-512 AIRFOIL (fx082512-il)
Reynolds number: 100,000
Max Cl/Cd: 46.6 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx082512-il-100000.txt
Download as CSV file: xf-fx082512-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.6222   0.08357   0.07859  -0.0571   1.0000   0.0860
  -9.750  -0.6260   0.07927   0.07429  -0.0562   1.0000   0.0841
  -9.500  -0.6475   0.07432   0.06939  -0.0562   1.0000   0.0826
  -9.250  -0.6808   0.06972   0.06483  -0.0560   1.0000   0.0811
  -9.000  -0.7138   0.06225   0.05726  -0.0627   1.0000   0.0789
  -8.750  -0.7274   0.05327   0.04781  -0.0748   1.0000   0.0772
  -8.500  -0.7176   0.04752   0.04156  -0.0812   1.0000   0.0783
  -8.250  -0.6969   0.04308   0.03655  -0.0865   1.0000   0.0817
  -8.000  -0.6664   0.03980   0.03239  -0.0922   1.0000   0.0853
  -7.750  -0.6429   0.03503   0.02752  -0.0945   1.0000   0.0901
  -7.500  -0.6157   0.03281   0.02504  -0.0961   1.0000   0.0969
  -7.250  -0.5871   0.03027   0.02219  -0.0978   1.0000   0.1029
  -7.000  -0.5626   0.02851   0.02047  -0.0980   1.0000   0.1103
  -6.750  -0.5358   0.02703   0.01882  -0.0986   1.0000   0.1171
  -6.500  -0.5134   0.02588   0.01787  -0.0979   1.0000   0.1242
  -6.250  -0.4873   0.02505   0.01698  -0.0980   1.0000   0.1309
  -6.000  -0.4621   0.02432   0.01645  -0.0979   1.0000   0.1382
  -5.750  -0.4321   0.02364   0.01576  -0.0992   1.0000   0.1463
  -5.500  -0.3975   0.02276   0.01487  -0.1019   1.0000   0.1565
  -5.250  -0.3548   0.02139   0.01384  -0.1071   1.0000   0.1901
  -5.000  -0.3340   0.02228   0.01522  -0.1054   1.0000   0.2711
  -4.750  -0.3131   0.02330   0.01605  -0.1037   1.0000   0.3038
  -4.500  -0.2969   0.02471   0.01742  -0.1007   1.0000   0.3223
  -4.250  -0.2825   0.02612   0.01885  -0.0973   1.0000   0.3360
  -4.000  -0.2678   0.02741   0.02014  -0.0941   1.0000   0.3486
  -3.750  -0.2478   0.02823   0.02083  -0.0926   1.0000   0.3610
  -3.500  -0.2393   0.02945   0.02222  -0.0877   1.0000   0.3669
  -3.250  -0.2157   0.02975   0.02237  -0.0876   1.0000   0.3772
  -3.000  -0.2058   0.03072   0.02347  -0.0834   1.0000   0.3836
  -2.750  -0.1847   0.03106   0.02372  -0.0827   1.0000   0.3938
  -2.500  -0.1716   0.03173   0.02445  -0.0797   1.0000   0.4010
  -2.250  -0.1473   0.03174   0.02437  -0.0801   1.0000   0.4095
  -2.000  -0.1335   0.03226   0.02495  -0.0774   1.0000   0.4163
  -1.750  -0.1025   0.03195   0.02446  -0.0800   1.0000   0.4238
  -1.500  -0.0867   0.03217   0.02475  -0.0781   1.0000   0.4275
  -1.250  -0.0635   0.03222   0.02476  -0.0784   1.0000   0.4333
  -1.000  -0.0404   0.03231   0.02481  -0.0787   1.0000   0.4411
  -0.750  -0.0112   0.03287   0.02539  -0.0796   0.9969   0.4501
  -0.500   0.0294   0.03336   0.02589  -0.0826   0.9899   0.4586
  -0.250   0.0723   0.03364   0.02612  -0.0865   0.9833   0.4661
   0.000   0.1200   0.03360   0.02596  -0.0920   0.9777   0.4706
   0.250   0.1567   0.03353   0.02590  -0.0947   0.9702   0.4726
   0.500   0.1972   0.03354   0.02590  -0.0982   0.9637   0.4745
   0.750   0.2392   0.03347   0.02581  -0.1021   0.9570   0.4758
   1.000   0.2778   0.03342   0.02574  -0.1053   0.9492   0.4773
   1.250   0.3310   0.03333   0.02563  -0.1108   0.9414   0.4797
   1.500   0.3937   0.03274   0.02501  -0.1175   0.9277   0.4837
   1.750   0.4547   0.03181   0.02413  -0.1231   0.9131   0.4868
   2.000   0.4991   0.03112   0.02355  -0.1259   0.8996   0.4892
   2.250   0.5660   0.02941   0.02197  -0.1314   0.8836   0.4928
   2.500   0.6196   0.02805   0.02072  -0.1350   0.8693   0.4972
   2.750   0.6672   0.02687   0.01964  -0.1376   0.8558   0.5016
   3.000   0.7159   0.02524   0.01824  -0.1396   0.8411   0.5055
   3.250   0.7752   0.02272   0.01595  -0.1425   0.8230   0.5102
   3.500   0.8145   0.02127   0.01463  -0.1426   0.7959   0.5144
   3.750   0.8644   0.01949   0.01295  -0.1440   0.7440   0.5192
   4.000   0.9209   0.01976   0.01148  -0.1463   0.4171   0.5257
   4.250   0.9243   0.02211   0.01245  -0.1423   0.2053   0.5293
   4.500   0.9421   0.02330   0.01323  -0.1407   0.1661   0.5334
   4.750   0.9594   0.02421   0.01409  -0.1387   0.1520   0.5373
   5.000   0.9784   0.02507   0.01499  -0.1370   0.1424   0.5419
   5.250   0.9982   0.02624   0.01609  -0.1357   0.1333   0.5471
   5.750   1.0572   0.02926   0.01902  -0.1364   0.1134   0.5602
   6.000   1.1002   0.03156   0.02129  -0.1390   0.1028   0.5691
   6.250   1.1473   0.03483   0.02444  -0.1427   0.0921   0.5802
   6.500   1.1748   0.03630   0.02634  -0.1418   0.0868   0.5891
   6.750   1.2071   0.03893   0.02900  -0.1428   0.0801   0.6003
   7.000   1.2349   0.04234   0.03281  -0.1424   0.0772   0.6128
   7.250   1.2548   0.04424   0.03526  -0.1401   0.0749   0.6269
   7.500   1.2729   0.04643   0.03797  -0.1379   0.0718   0.6440
   7.750   1.2901   0.04935   0.04141  -0.1356   0.0707   0.6657
   8.000   1.3038   0.05302   0.04572  -0.1327   0.0720   0.6962
   8.250   1.3124   0.05688   0.05025  -0.1291   0.0741   0.7561
   8.500   1.3121   0.05995   0.05382  -0.1242   0.0754   1.0000
  10.750   0.8702   0.13810   0.13498  -0.1159   0.1780   0.6346
  11.000   0.8942   0.13998   0.13703  -0.1130   0.1658   0.6621
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