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


Details Polar file
Airfoil: FX 60-100 AIRFOIL (fx60100-il)
Reynolds number: 100,000
Max Cl/Cd: 61.36 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx60100-il-100000-n5.txt
Download as CSV file: xf-fx60100-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3672   0.09245   0.08744  -0.0393   1.0000   0.0235
  -8.750  -0.3700   0.08869   0.08376  -0.0402   1.0000   0.0228
  -8.500  -0.3755   0.08471   0.07987  -0.0411   1.0000   0.0222
  -8.250  -0.3849   0.08048   0.07575  -0.0419   1.0000   0.0214
  -7.750  -0.4292   0.06826   0.06376  -0.0448   1.0000   0.0195
  -7.500  -0.4417   0.06440   0.05996  -0.0461   1.0000   0.0193
  -7.250  -0.4513   0.05988   0.05544  -0.0496   1.0000   0.0191
  -7.000  -0.4573   0.05449   0.04991  -0.0547   1.0000   0.0190
  -6.750  -0.4398   0.04783   0.04286  -0.0635   0.9960   0.0187
  -6.500  -0.4090   0.04136   0.03579  -0.0723   0.9906   0.0187
  -6.250  -0.3724   0.03649   0.03002  -0.0790   0.9860   0.0196
  -6.000  -0.3390   0.03246   0.02562  -0.0836   0.9825   0.0207
  -5.750  -0.3061   0.02975   0.02249  -0.0863   0.9779   0.0214
  -5.500  -0.2708   0.02719   0.01950  -0.0888   0.9741   0.0216
  -5.250  -0.2345   0.02512   0.01710  -0.0911   0.9711   0.0220
  -5.000  -0.2021   0.02351   0.01526  -0.0923   0.9666   0.0226
  -4.750  -0.1685   0.02213   0.01370  -0.0937   0.9618   0.0235
  -4.500  -0.1314   0.02094   0.01236  -0.0957   0.9579   0.0248
  -4.250  -0.0963   0.01998   0.01123  -0.0973   0.9530   0.0265
  -4.000  -0.0619   0.01910   0.01027  -0.0991   0.9476   0.0312
  -3.750  -0.0233   0.01822   0.00924  -0.1016   0.9438   0.0404
  -3.500   0.0156   0.01681   0.00817  -0.1045   0.9401   0.1156
  -3.250   0.0489   0.01564   0.00812  -0.1069   0.9340   0.3651
  -3.000   0.0865   0.01559   0.00805  -0.1085   0.9292   0.4236
  -2.750   0.1180   0.01558   0.00795  -0.1090   0.9222   0.4546
  -2.500   0.1518   0.01556   0.00783  -0.1100   0.9163   0.4813
  -2.250   0.1852   0.01553   0.00775  -0.1108   0.9109   0.5037
  -2.000   0.2153   0.01551   0.00763  -0.1110   0.9034   0.5221
  -1.750   0.2515   0.01539   0.00743  -0.1123   0.8986   0.5378
  -1.500   0.2795   0.01535   0.00734  -0.1121   0.8891   0.5525
  -1.250   0.3129   0.01523   0.00717  -0.1129   0.8823   0.5674
  -1.000   0.3425   0.01515   0.00705  -0.1129   0.8735   0.5803
  -0.750   0.3729   0.01506   0.00695  -0.1131   0.8656   0.5921
  -0.500   0.4038   0.01495   0.00682  -0.1134   0.8574   0.6049
  -0.250   0.4322   0.01488   0.00674  -0.1131   0.8470   0.6187
   0.000   0.4622   0.01475   0.00661  -0.1131   0.8373   0.6326
   0.250   0.4922   0.01464   0.00650  -0.1131   0.8276   0.6459
   0.500   0.5196   0.01459   0.00648  -0.1128   0.8162   0.6593
   0.750   0.5478   0.01452   0.00643  -0.1124   0.8048   0.6733
   1.000   0.5759   0.01442   0.00636  -0.1121   0.7924   0.6883
   1.250   0.6035   0.01433   0.00632  -0.1116   0.7794   0.7049
   1.500   0.6307   0.01424   0.00629  -0.1110   0.7661   0.7241
   1.750   0.6573   0.01416   0.00628  -0.1103   0.7524   0.7457
   2.250   0.7071   0.01394   0.00627  -0.1081   0.7207   0.8039
   2.500   0.7287   0.01374   0.00622  -0.1062   0.7040   0.8629
   2.750   0.7572   0.01366   0.00614  -0.1059   0.6849   1.0000
   3.000   0.7853   0.01378   0.00617  -0.1057   0.6624   1.0000
   3.250   0.8128   0.01393   0.00624  -0.1054   0.6376   1.0000
   3.500   0.8397   0.01414   0.00635  -0.1049   0.6122   1.0000
   3.750   0.8661   0.01439   0.00651  -0.1045   0.5874   1.0000
   4.000   0.8922   0.01467   0.00671  -0.1040   0.5625   1.0000
   4.250   0.9177   0.01500   0.00697  -0.1034   0.5359   1.0000
   4.500   0.9425   0.01536   0.00726  -0.1027   0.5075   1.0000
   4.750   0.9667   0.01577   0.00757  -0.1020   0.4772   1.0000
   5.000   0.9906   0.01620   0.00793  -0.1012   0.4459   1.0000
   5.250   1.0140   0.01668   0.00835  -0.1004   0.4143   1.0000
   5.500   1.0369   0.01721   0.00880  -0.0996   0.3822   1.0000
   5.750   1.0590   0.01781   0.00929  -0.0987   0.3490   1.0000
   6.000   1.0808   0.01845   0.00985  -0.0978   0.3140   1.0000
   6.250   1.1013   0.01921   0.01050  -0.0967   0.2793   1.0000
   6.500   1.1215   0.02002   0.01120  -0.0957   0.2425   1.0000
   6.750   1.1403   0.02097   0.01199  -0.0946   0.2077   1.0000
   7.000   1.1587   0.02197   0.01284  -0.0934   0.1774   1.0000
   7.500   1.1952   0.02401   0.01477  -0.0910   0.1325   1.0000
   7.750   1.2129   0.02505   0.01581  -0.0898   0.1170   1.0000
   8.000   1.2304   0.02609   0.01688  -0.0885   0.1048   1.0000
   8.250   1.2466   0.02721   0.01802  -0.0870   0.0962   1.0000
   8.500   1.2620   0.02838   0.01925  -0.0855   0.0890   1.0000
   8.750   1.2763   0.02966   0.02059  -0.0838   0.0831   1.0000
   9.000   1.2914   0.03085   0.02192  -0.0822   0.0772   1.0000
   9.250   1.3041   0.03219   0.02334  -0.0804   0.0727   1.0000
   9.500   1.3180   0.03338   0.02472  -0.0787   0.0681   1.0000
   9.750   1.3297   0.03468   0.02611  -0.0768   0.0648   1.0000
  10.000   1.3398   0.03628   0.02771  -0.0749   0.0624   1.0000
  10.250   1.3539   0.03784   0.02951  -0.0734   0.0602   1.0000
  10.500   1.3675   0.03952   0.03141  -0.0718   0.0579   1.0000
  10.750   1.3792   0.04123   0.03329  -0.0703   0.0556   1.0000
  11.000   1.3864   0.04287   0.03501  -0.0685   0.0527   1.0000
  11.250   1.3913   0.04480   0.03710  -0.0668   0.0493   1.0000
  11.500   1.3929   0.04644   0.03906  -0.0650   0.0450   1.0000
  11.750   1.3922   0.04819   0.04096  -0.0637   0.0412   1.0000
  12.000   1.3926   0.05037   0.04337  -0.0626   0.0376   1.0000
  12.250   1.3942   0.05262   0.04586  -0.0619   0.0340   1.0000
  12.500   1.3924   0.05524   0.04862  -0.0614   0.0314   1.0000
  12.750   1.3893   0.05849   0.05206  -0.0612   0.0290   1.0000
  13.000   1.3862   0.06195   0.05581  -0.0612   0.0258   1.0000
  13.250   1.3801   0.06585   0.05988  -0.0619   0.0236   1.0000
  13.500   1.3699   0.07056   0.06472  -0.0631   0.0223   1.0000
  13.750   1.3591   0.07584   0.07024  -0.0645   0.0208   1.0000
  14.000   1.3466   0.08169   0.07637  -0.0665   0.0196   1.0000
  14.250   1.3325   0.08808   0.08301  -0.0691   0.0187   1.0000
  14.500   1.3173   0.09510   0.09025  -0.0725   0.0181   1.0000
  14.750   1.3008   0.10273   0.09810  -0.0765   0.0178   1.0000
  15.000   1.2829   0.11112   0.10670  -0.0812   0.0176   1.0000
  15.250   1.2634   0.12036   0.11615  -0.0866   0.0177   1.0000
  15.500   1.2417   0.13073   0.12673  -0.0930   0.0181   1.0000
  15.750   1.2172   0.14251   0.13871  -0.1003   0.0188   1.0000
  16.000   1.1918   0.15531   0.15165  -0.1082   0.0201   1.0000
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