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FX 63-100 AIRFOIL (fx63100-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 63-100 AIRFOIL (fx63100-il)
Reynolds number: 50,000
Max Cl/Cd: 44.35 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63100-il-50000-n5.txt
Download as CSV file: xf-fx63100-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-100 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3410   0.12201   0.11470  -0.0372   1.0000   0.1030
  -9.750  -0.3461   0.11992   0.11271  -0.0387   1.0000   0.1037
  -9.500  -0.3509   0.11758   0.11048  -0.0399   1.0000   0.1041
  -9.250  -0.3537   0.11488   0.10787  -0.0405   1.0000   0.1042
  -8.250  -0.3557   0.09703   0.09028  -0.0421   1.0000   0.0613
  -8.000  -0.3599   0.09442   0.08777  -0.0409   1.0000   0.0610
  -7.750  -0.3653   0.09201   0.08547  -0.0394   1.0000   0.0607
  -7.500  -0.3714   0.08960   0.08317  -0.0379   1.0000   0.0602
  -7.250  -0.3782   0.08697   0.08065  -0.0372   1.0000   0.0599
  -7.000  -0.3852   0.08413   0.07792  -0.0370   1.0000   0.0595
  -6.750  -0.3906   0.08117   0.07504  -0.0373   1.0000   0.0588
  -6.500  -0.3947   0.07768   0.07162  -0.0387   1.0000   0.0582
  -6.250  -0.3956   0.07347   0.06744  -0.0417   1.0000   0.0575
  -6.000  -0.3919   0.06827   0.06222  -0.0466   1.0000   0.0567
  -5.750  -0.3815   0.06242   0.05624  -0.0529   0.9998   0.0561
  -5.500  -0.3394   0.05372   0.04703  -0.0675   0.9941   0.0574
  -5.250  -0.2871   0.04544   0.03776  -0.0816   0.9898   0.0605
  -5.000  -0.2395   0.04011   0.03163  -0.0898   0.9866   0.0624
  -4.750  -0.2039   0.03795   0.02932  -0.0933   0.9814   0.0675
  -4.500  -0.1576   0.03475   0.02535  -0.0987   0.9778   0.0726
  -4.250  -0.1186   0.03258   0.02278  -0.1021   0.9730   0.0783
  -4.000  -0.0795   0.03096   0.02078  -0.1050   0.9683   0.0849
  -3.750  -0.0425   0.02945   0.01888  -0.1069   0.9631   0.0902
  -3.500  -0.0076   0.02844   0.01777  -0.1088   0.9574   0.1000
  -3.250   0.0261   0.02744   0.01659  -0.1099   0.9517   0.1070
  -3.000   0.0602   0.02663   0.01565  -0.1113   0.9453   0.1169
  -2.750   0.0990   0.02582   0.01483  -0.1139   0.9403   0.1363
  -2.500   0.1359   0.02502   0.01405  -0.1163   0.9334   0.1632
  -2.250   0.1824   0.02367   0.01365  -0.1213   0.9293   0.3117
  -2.000   0.2134   0.02343   0.01404  -0.1217   0.9219   0.4905
  -1.750   0.2456   0.02364   0.01428  -0.1219   0.9145   0.5811
  -1.500   0.2705   0.02386   0.01455  -0.1206   0.9056   0.6438
  -1.250   0.2980   0.02394   0.01466  -0.1194   0.8983   0.6973
  -1.000   0.3205   0.02399   0.01468  -0.1178   0.8885   0.7370
  -0.750   0.3534   0.02382   0.01443  -0.1180   0.8821   0.7693
  -0.250   0.4127   0.02354   0.01400  -0.1180   0.8656   0.8221
   0.000   0.4335   0.02348   0.01392  -0.1165   0.8548   0.8513
   0.250   0.4590   0.02329   0.01372  -0.1157   0.8460   0.8896
   0.500   0.4934   0.02303   0.01344  -0.1169   0.8371   1.0000
   0.750   0.5301   0.02329   0.01356  -0.1192   0.8274   1.0000
   1.000   0.5736   0.02335   0.01348  -0.1223   0.8208   1.0000
   1.250   0.6058   0.02367   0.01372  -0.1236   0.8100   1.0000
   1.500   0.6452   0.02375   0.01372  -0.1257   0.8025   1.0000
   1.750   0.6776   0.02401   0.01394  -0.1268   0.7921   1.0000
   2.000   0.7090   0.02429   0.01419  -0.1276   0.7816   1.0000
   2.250   0.7479   0.02428   0.01416  -0.1292   0.7740   1.0000
   2.750   0.8055   0.02492   0.01483  -0.1297   0.7505   1.0000
   3.000   0.8399   0.02498   0.01493  -0.1304   0.7409   1.0000
   3.250   0.8709   0.02515   0.01514  -0.1307   0.7294   1.0000
   3.500   0.8988   0.02542   0.01550  -0.1306   0.7163   1.0000
   3.750   0.9277   0.02559   0.01573  -0.1304   0.7027   1.0000
   4.000   0.9571   0.02565   0.01586  -0.1301   0.6880   1.0000
   4.250   0.9863   0.02566   0.01597  -0.1296   0.6723   1.0000
   4.500   1.0149   0.02569   0.01608  -0.1291   0.6560   1.0000
   4.750   1.0431   0.02577   0.01625  -0.1285   0.6395   1.0000
   5.000   1.0710   0.02587   0.01647  -0.1279   0.6228   1.0000
   5.250   1.0985   0.02599   0.01668  -0.1272   0.6054   1.0000
   5.500   1.1215   0.02634   0.01717  -0.1261   0.5855   1.0000
   5.750   1.1463   0.02658   0.01753  -0.1251   0.5651   1.0000
   6.000   1.1699   0.02676   0.01781  -0.1237   0.5409   1.0000
   6.250   1.1911   0.02696   0.01803  -0.1219   0.5108   1.0000
   6.500   1.2103   0.02729   0.01833  -0.1198   0.4766   1.0000
   6.750   1.2289   0.02778   0.01876  -0.1179   0.4425   1.0000
   7.000   1.2464   0.02847   0.01944  -0.1159   0.4094   1.0000
   7.250   1.2608   0.02937   0.02032  -0.1138   0.3735   1.0000
   7.500   1.2716   0.03046   0.02129  -0.1113   0.3329   1.0000
   7.750   1.2791   0.03181   0.02245  -0.1086   0.2896   1.0000
   8.000   1.2840   0.03341   0.02382  -0.1058   0.2495   1.0000
   8.250   1.2868   0.03521   0.02540  -0.1029   0.2165   1.0000
   8.500   1.2911   0.03713   0.02721  -0.1004   0.1894   1.0000
   8.750   1.2953   0.03916   0.02919  -0.0982   0.1678   1.0000
   9.000   1.3009   0.04122   0.03124  -0.0961   0.1500   1.0000
   9.250   1.3072   0.04335   0.03337  -0.0943   0.1368   1.0000
   9.500   1.3141   0.04552   0.03552  -0.0926   0.1267   1.0000
   9.750   1.3243   0.04759   0.03769  -0.0911   0.1174   1.0000
  10.000   1.3362   0.04965   0.03985  -0.0897   0.1095   1.0000
  10.250   1.3465   0.05175   0.04196  -0.0885   0.1026   1.0000
  10.500   1.3611   0.05382   0.04425  -0.0873   0.0961   1.0000
  10.750   1.3780   0.05585   0.04643  -0.0863   0.0913   1.0000
  11.000   1.4005   0.05799   0.04866  -0.0855   0.0872   1.0000
  11.250   1.4130   0.06064   0.05170  -0.0844   0.0830   1.0000
  11.500   1.4215   0.06324   0.05447  -0.0834   0.0789   1.0000
  11.750   1.4387   0.06588   0.05710  -0.0827   0.0753   1.0000
  12.000   1.4373   0.06959   0.06131  -0.0815   0.0731   1.0000
  12.250   1.4322   0.07353   0.06566  -0.0805   0.0708   1.0000
  12.500   1.4254   0.07758   0.07001  -0.0799   0.0684   1.0000
  12.750   1.4202   0.08153   0.07418  -0.0796   0.0662   1.0000
  13.000   1.4217   0.08506   0.07783  -0.0794   0.0639   1.0000
  13.250   1.4111   0.09013   0.08314  -0.0798   0.0627   1.0000
  13.500   1.3891   0.09653   0.08991  -0.0814   0.0622   1.0000
  13.750   1.3659   0.10360   0.09731  -0.0840   0.0619   1.0000
  14.000   1.3404   0.11158   0.10552  -0.0878   0.0618   1.0000
  14.250   1.3136   0.12058   0.11477  -0.0930   0.0620   1.0000
  14.500   1.2862   0.13073   0.12511  -0.0994   0.0624   1.0000
  14.750   1.2581   0.14240   0.13692  -0.1073   0.0628   1.0000
  15.000   1.2309   0.15544   0.15002  -0.1162   0.0632   1.0000
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