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FX 60-100 AIRFOIL (fx60100-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: FX 60-100 AIRFOIL (fx60100-il)
Reynolds number: 500,000
Max Cl/Cd: 87.6 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx60100-il-500000-n5.txt
Download as CSV file: xf-fx60100-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-100 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3828   0.08353   0.08132  -0.0399   1.0000   0.0078
  -8.750  -0.3927   0.07889   0.07673  -0.0408   1.0000   0.0074
  -8.500  -0.3973   0.07269   0.07057  -0.0450   0.9977   0.0073
  -8.250  -0.4185   0.04383   0.04143  -0.0779   0.9769   0.0062
  -8.000  -0.3909   0.03321   0.03020  -0.0989   0.9675   0.0062
  -7.750  -0.3668   0.02776   0.02422  -0.1054   0.9597   0.0061
  -7.500  -0.3393   0.02398   0.01997  -0.1092   0.9543   0.0060
  -7.250  -0.3131   0.02130   0.01691  -0.1110   0.9473   0.0060
  -7.000  -0.2839   0.01915   0.01440  -0.1126   0.9420   0.0061
  -6.750  -0.2573   0.01760   0.01257  -0.1131   0.9344   0.0062
  -6.500  -0.2289   0.01636   0.01109  -0.1137   0.9281   0.0063
  -6.250  -0.2023   0.01490   0.00941  -0.1140   0.9205   0.0065
  -6.000  -0.1749   0.01368   0.00805  -0.1144   0.9138   0.0068
  -5.750  -0.1475   0.01292   0.00721  -0.1146   0.9064   0.0071
  -5.500  -0.1196   0.01229   0.00650  -0.1148   0.8996   0.0074
  -5.250  -0.0916   0.01172   0.00583  -0.1149   0.8922   0.0078
  -5.000  -0.0633   0.01123   0.00525  -0.1151   0.8856   0.0082
  -4.750  -0.0350   0.01085   0.00481  -0.1153   0.8791   0.0089
  -4.500  -0.0065   0.01048   0.00435  -0.1154   0.8726   0.0093
  -4.250   0.0222   0.01008   0.00387  -0.1156   0.8663   0.0095
  -4.000   0.0511   0.00967   0.00335  -0.1158   0.8594   0.0098
  -3.750   0.0799   0.00936   0.00294  -0.1160   0.8526   0.0104
  -3.500   0.1085   0.00913   0.00262  -0.1160   0.8445   0.0114
  -3.250   0.1371   0.00894   0.00236  -0.1161   0.8367   0.0133
  -3.000   0.1659   0.00860   0.00207  -0.1163   0.8288   0.0423
  -2.750   0.1948   0.00821   0.00185  -0.1166   0.8207   0.1002
  -2.250   0.2525   0.00725   0.00154  -0.1177   0.8022   0.3156
  -2.000   0.2808   0.00716   0.00148  -0.1177   0.7923   0.3479
  -1.750   0.3090   0.00714   0.00142  -0.1176   0.7819   0.3656
  -1.500   0.3371   0.00711   0.00138  -0.1175   0.7692   0.3843
  -1.250   0.3650   0.00711   0.00134  -0.1174   0.7544   0.4028
  -1.000   0.3927   0.00713   0.00131  -0.1172   0.7348   0.4180
  -0.750   0.4200   0.00718   0.00130  -0.1170   0.7134   0.4358
  -0.500   0.4475   0.00723   0.00130  -0.1168   0.6930   0.4528
  -0.250   0.4750   0.00731   0.00131  -0.1166   0.6724   0.4661
   0.000   0.5023   0.00740   0.00134  -0.1163   0.6522   0.4791
   0.250   0.5295   0.00750   0.00138  -0.1161   0.6293   0.4940
   0.500   0.5562   0.00766   0.00144  -0.1158   0.6005   0.5079
   0.750   0.5827   0.00785   0.00152  -0.1155   0.5699   0.5184
   1.000   0.6092   0.00804   0.00160  -0.1152   0.5416   0.5282
   1.250   0.6361   0.00822   0.00170  -0.1150   0.5170   0.5382
   1.500   0.6631   0.00837   0.00180  -0.1148   0.4961   0.5481
   1.750   0.6903   0.00852   0.00190  -0.1146   0.4786   0.5584
   2.000   0.7175   0.00867   0.00203  -0.1144   0.4611   0.5697
   2.250   0.7444   0.00884   0.00216  -0.1143   0.4402   0.5808
   2.500   0.7709   0.00906   0.00230  -0.1140   0.4147   0.5907
   2.750   0.7973   0.00929   0.00246  -0.1138   0.3908   0.6009
   3.250   0.8499   0.00978   0.00284  -0.1133   0.3412   0.6238
   3.500   0.8761   0.01003   0.00304  -0.1130   0.3175   0.6377
   4.000   0.9277   0.01059   0.00352  -0.1124   0.2682   0.6693
   4.250   0.9530   0.01092   0.00379  -0.1120   0.2398   0.6873
   4.500   0.9780   0.01127   0.00409  -0.1116   0.2127   0.7086
   4.750   1.0020   0.01172   0.00445  -0.1111   0.1780   0.7350
   5.000   1.0260   0.01211   0.00481  -0.1105   0.1486   0.7700
   5.250   1.0482   0.01235   0.00515  -0.1095   0.1305   0.8336
   5.500   1.0685   0.01244   0.00537  -0.1078   0.1201   1.0000
   5.750   1.0936   0.01283   0.00571  -0.1075   0.1047   1.0000
   6.000   1.1182   0.01327   0.00609  -0.1070   0.0928   1.0000
   6.250   1.1431   0.01367   0.00646  -0.1066   0.0849   1.0000
   6.500   1.1682   0.01401   0.00682  -0.1062   0.0760   1.0000
   6.750   1.1924   0.01446   0.00723  -0.1057   0.0657   1.0000
   7.000   1.2164   0.01492   0.00766  -0.1052   0.0593   1.0000
   7.250   1.2397   0.01543   0.00816  -0.1046   0.0532   1.0000
   7.500   1.2638   0.01583   0.00860  -0.1040   0.0483   1.0000
   7.750   1.2868   0.01634   0.00910  -0.1034   0.0408   1.0000
   8.000   1.3098   0.01683   0.00960  -0.1027   0.0366   1.0000
   8.250   1.3322   0.01735   0.01012  -0.1020   0.0328   1.0000
   8.500   1.3544   0.01788   0.01069  -0.1012   0.0298   1.0000
   8.750   1.3765   0.01839   0.01124  -0.1004   0.0272   1.0000
   9.000   1.3976   0.01897   0.01185  -0.0995   0.0244   1.0000
   9.250   1.4182   0.01958   0.01248  -0.0986   0.0214   1.0000
   9.500   1.4375   0.02025   0.01315  -0.0975   0.0160   1.0000
   9.750   1.4510   0.02148   0.01427  -0.0956   0.0055   1.0000
  10.000   1.4668   0.02242   0.01527  -0.0940   0.0041   1.0000
  10.250   1.4818   0.02335   0.01629  -0.0922   0.0035   1.0000
  10.500   1.4941   0.02430   0.01736  -0.0900   0.0031   1.0000
  10.750   1.5061   0.02517   0.01834  -0.0878   0.0030   1.0000
  11.000   1.5170   0.02612   0.01940  -0.0856   0.0028   1.0000
  11.250   1.5269   0.02717   0.02056  -0.0833   0.0027   1.0000
  11.500   1.5356   0.02833   0.02185  -0.0811   0.0026   1.0000
  11.750   1.5434   0.02962   0.02325  -0.0789   0.0025   1.0000
  12.000   1.5502   0.03103   0.02479  -0.0769   0.0024   1.0000
  12.250   1.5557   0.03261   0.02651  -0.0749   0.0023   1.0000
  12.500   1.5599   0.03438   0.02841  -0.0730   0.0022   1.0000
  12.750   1.5628   0.03633   0.03050  -0.0713   0.0021   1.0000
  13.000   1.5637   0.03858   0.03291  -0.0697   0.0021   1.0000
  13.250   1.5628   0.04112   0.03560  -0.0683   0.0020   1.0000
  13.500   1.5598   0.04401   0.03865  -0.0672   0.0020   1.0000
  13.750   1.5547   0.04732   0.04212  -0.0665   0.0019   1.0000
  14.000   1.5472   0.05114   0.04610  -0.0662   0.0019   1.0000
  14.250   1.5380   0.05544   0.05057  -0.0665   0.0019   1.0000
  14.500   1.5274   0.06022   0.05553  -0.0673   0.0018   1.0000
  14.750   1.5156   0.06553   0.06100  -0.0688   0.0018   1.0000
  15.000   1.5047   0.07105   0.06669  -0.0707   0.0018   1.0000
  15.250   1.4921   0.07720   0.07301  -0.0732   0.0018   1.0000
  15.500   1.4781   0.08396   0.07994  -0.0762   0.0018   1.0000
  15.750   1.4619   0.09148   0.08763  -0.0799   0.0018   1.0000
  16.000   1.4445   0.09959   0.09591  -0.0840   0.0018   1.0000
  16.250   1.4255   0.10837   0.10486  -0.0887   0.0018   1.0000
  16.500   1.4055   0.11765   0.11432  -0.0939   0.0018   1.0000
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