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FX60-100 10.0% smoothed (fx60100sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX60-100 10.0% smoothed (fx60100sm-il)
Reynolds number: 100,000
Max Cl/Cd: 61.57 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx60100sm-il-100000-n5.txt
Download as CSV file: xf-fx60100sm-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX60-100 10.0% smoothed                         
  
 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  -0.3807   0.08919   0.08418  -0.0425   1.0000   0.0261
  -8.750  -0.3811   0.08618   0.08124  -0.0424   1.0000   0.0257
  -8.500  -0.3838   0.08304   0.07817  -0.0425   1.0000   0.0253
  -8.250  -0.3893   0.07992   0.07511  -0.0424   1.0000   0.0250
  -8.000  -0.3995   0.07679   0.07209  -0.0419   1.0000   0.0246
  -7.750  -0.4145   0.07391   0.06935  -0.0407   1.0000   0.0243
  -7.500  -0.4287   0.07016   0.06570  -0.0409   1.0000   0.0240
  -7.250  -0.4410   0.06486   0.06045  -0.0439   1.0000   0.0235
  -7.000  -0.4510   0.05778   0.05330  -0.0512   1.0000   0.0230
  -6.750  -0.4447   0.05040   0.04559  -0.0599   0.9979   0.0224
  -6.500  -0.4131   0.04324   0.03783  -0.0703   0.9922   0.0226
  -6.250  -0.3790   0.03826   0.03223  -0.0770   0.9872   0.0239
  -6.000  -0.3418   0.03417   0.02744  -0.0823   0.9835   0.0248
  -5.750  -0.3076   0.03092   0.02364  -0.0855   0.9791   0.0249
  -5.500  -0.2726   0.02827   0.02051  -0.0881   0.9749   0.0251
  -5.250  -0.2361   0.02611   0.01793  -0.0904   0.9715   0.0256
  -5.000  -0.2007   0.02443   0.01593  -0.0922   0.9678   0.0261
  -4.750  -0.1693   0.02279   0.01414  -0.0932   0.9627   0.0270
  -4.500  -0.1347   0.02147   0.01283  -0.0951   0.9586   0.0298
  -4.250  -0.0970   0.02051   0.01177  -0.0974   0.9553   0.0333
  -4.000  -0.0658   0.01969   0.01081  -0.0982   0.9488   0.0355
  -3.750  -0.0285   0.01866   0.00967  -0.1005   0.9443   0.0403
  -3.500   0.0120   0.01782   0.00874  -0.1033   0.9409   0.0522
  -3.250   0.0457   0.01647   0.00786  -0.1054   0.9346   0.1446
  -3.000   0.0824   0.01556   0.00782  -0.1079   0.9298   0.3714
  -2.750   0.1185   0.01564   0.00805  -0.1093   0.9251   0.4552
  -2.500   0.1483   0.01561   0.00792  -0.1095   0.9169   0.4787
  -2.250   0.1847   0.01551   0.00771  -0.1108   0.9120   0.4978
  -2.000   0.2136   0.01546   0.00759  -0.1109   0.9033   0.5146
  -1.750   0.2491   0.01533   0.00739  -0.1120   0.8978   0.5313
  -1.500   0.2778   0.01527   0.00727  -0.1120   0.8887   0.5458
  -1.250   0.3125   0.01512   0.00707  -0.1130   0.8827   0.5604
  -1.000   0.3404   0.01506   0.00699  -0.1127   0.8728   0.5739
  -0.750   0.3721   0.01493   0.00684  -0.1131   0.8651   0.5879
  -0.500   0.4018   0.01483   0.00673  -0.1132   0.8559   0.6019
  -0.250   0.4304   0.01475   0.00666  -0.1130   0.8459   0.6160
   0.000   0.4615   0.01462   0.00652  -0.1132   0.8373   0.6308
   0.250   0.4898   0.01454   0.00646  -0.1129   0.8265   0.6460
   0.500   0.5177   0.01447   0.00641  -0.1126   0.8151   0.6619
   0.750   0.5461   0.01439   0.00636  -0.1123   0.8038   0.6790
   1.000   0.5747   0.01430   0.00630  -0.1120   0.7924   0.6975
   1.250   0.6025   0.01418   0.00623  -0.1115   0.7805   0.7169
   1.500   0.6292   0.01410   0.00621  -0.1108   0.7669   0.7393
   1.750   0.6550   0.01400   0.00621  -0.1099   0.7528   0.7649
   2.000   0.6798   0.01388   0.00618  -0.1088   0.7380   0.7975
   2.500   0.7288   0.01355   0.00605  -0.1063   0.7056   1.0000
   2.750   0.7576   0.01368   0.00615  -0.1063   0.6877   1.0000
   3.000   0.7859   0.01382   0.00622  -0.1062   0.6689   1.0000
   3.250   0.8138   0.01398   0.00630  -0.1060   0.6491   1.0000
   3.500   0.8406   0.01417   0.00644  -0.1056   0.6267   1.0000
   3.750   0.8671   0.01439   0.00661  -0.1051   0.6024   1.0000
   4.000   0.8929   0.01465   0.00677  -0.1044   0.5750   1.0000
   4.250   0.9179   0.01496   0.00697  -0.1037   0.5454   1.0000
   4.500   0.9425   0.01531   0.00722  -0.1029   0.5151   1.0000
   4.750   0.9667   0.01570   0.00754  -0.1022   0.4844   1.0000
   5.000   0.9905   0.01614   0.00789  -0.1014   0.4530   1.0000
   5.250   1.0136   0.01663   0.00827  -0.1005   0.4202   1.0000
   5.500   1.0361   0.01717   0.00873  -0.0996   0.3862   1.0000
   5.750   1.0581   0.01776   0.00922  -0.0987   0.3503   1.0000
   6.000   1.0792   0.01844   0.00976  -0.0977   0.3138   1.0000
   6.250   1.0995   0.01921   0.01038  -0.0966   0.2753   1.0000
   6.500   1.1192   0.02006   0.01108  -0.0955   0.2379   1.0000
   6.750   1.1385   0.02098   0.01189  -0.0944   0.2059   1.0000
   7.000   1.1575   0.02192   0.01274  -0.0933   0.1798   1.0000
   7.250   1.1758   0.02294   0.01366  -0.0921   0.1593   1.0000
   7.500   1.1943   0.02391   0.01461  -0.0909   0.1432   1.0000
   7.750   1.2120   0.02495   0.01563  -0.0896   0.1315   1.0000
   8.000   1.2302   0.02594   0.01672  -0.0883   0.1214   1.0000
   8.250   1.2476   0.02698   0.01782  -0.0870   0.1128   1.0000
   8.500   1.2631   0.02814   0.01897  -0.0855   0.1056   1.0000
   8.750   1.2807   0.02920   0.02018  -0.0842   0.0991   1.0000
   9.000   1.2955   0.03040   0.02142  -0.0826   0.0932   1.0000
   9.250   1.3117   0.03156   0.02273  -0.0812   0.0871   1.0000
   9.500   1.3256   0.03276   0.02405  -0.0796   0.0816   1.0000
   9.750   1.3381   0.03407   0.02547  -0.0778   0.0764   1.0000
  10.000   1.3496   0.03526   0.02682  -0.0760   0.0707   1.0000
  10.250   1.3580   0.03673   0.02832  -0.0740   0.0661   1.0000
  10.500   1.3685   0.03805   0.02991  -0.0721   0.0605   1.0000
  10.750   1.3742   0.03956   0.03149  -0.0702   0.0562   1.0000
  11.000   1.3815   0.04126   0.03342  -0.0684   0.0513   1.0000
  11.250   1.3864   0.04299   0.03531  -0.0667   0.0470   1.0000
  11.500   1.3880   0.04512   0.03754  -0.0651   0.0436   1.0000
  11.750   1.3922   0.04734   0.04005  -0.0637   0.0395   1.0000
  12.000   1.3927   0.04967   0.04251  -0.0625   0.0365   1.0000
  12.250   1.3903   0.05252   0.04545  -0.0615   0.0341   1.0000
  12.500   1.3900   0.05555   0.04878  -0.0607   0.0314   1.0000
  12.750   1.3869   0.05884   0.05226  -0.0602   0.0294   1.0000
  13.000   1.3822   0.06237   0.05594  -0.0602   0.0279   1.0000
  13.250   1.3748   0.06640   0.06008  -0.0607   0.0268   1.0000
  13.500   1.3670   0.07095   0.06486  -0.0613   0.0256   1.0000
  13.750   1.3579   0.07590   0.07011  -0.0625   0.0245   1.0000
  14.000   1.3472   0.08131   0.07577  -0.0643   0.0236   1.0000
  14.250   1.3348   0.08720   0.08189  -0.0666   0.0229   1.0000
  14.500   1.3214   0.09362   0.08852  -0.0696   0.0224   1.0000
  14.750   1.3067   0.10067   0.09578  -0.0732   0.0220   1.0000
  15.000   1.2902   0.10847   0.10379  -0.0776   0.0218   1.0000
  15.250   1.2711   0.11736   0.11291  -0.0828   0.0218   1.0000
  15.500   1.2469   0.12820   0.12400  -0.0896   0.0221   1.0000
  15.750   1.2085   0.14393   0.13999  -0.0996   0.0234   1.0000
  16.000   1.1697   0.16157   0.15776  -0.1108   0.0250   1.0000
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