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FX 61-163 AIRFOIL (fx61163-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 61-163 AIRFOIL (fx61163-il)
Reynolds number: 50,000
Max Cl/Cd: 19.36 at α=11.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx61163-il-50000-n5.txt
Download as CSV file: xf-fx61163-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 61-163 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4019   0.10472   0.09779  -0.0500   1.0001   0.0396
 -11.000  -0.4087   0.09834   0.09147  -0.0534   1.0001   0.0390
 -10.750  -0.4212   0.09160   0.08480  -0.0572   1.0001   0.0382
 -10.500  -0.4404   0.08485   0.07806  -0.0612   1.0001   0.0372
 -10.250  -0.4631   0.07891   0.07211  -0.0641   1.0001   0.0364
 -10.000  -0.4882   0.07392   0.06706  -0.0657   1.0001   0.0356
  -9.750  -0.5139   0.07000   0.06308  -0.0656   1.0001   0.0351
  -9.500  -0.5407   0.06707   0.06009  -0.0637   1.0001   0.0346
  -9.250  -0.5633   0.06443   0.05738  -0.0616   1.0001   0.0343
  -9.000  -0.5801   0.06212   0.05500  -0.0591   1.0001   0.0343
  -8.750  -0.5965   0.06031   0.05313  -0.0559   1.0001   0.0343
  -8.500  -0.5945   0.05763   0.05029  -0.0561   0.9932   0.0348
  -8.250  -0.5718   0.05392   0.04627  -0.0599   0.9771   0.0360
  -8.000  -0.5477   0.05039   0.04233  -0.0631   0.9615   0.0373
  -7.750  -0.5210   0.04703   0.03847  -0.0656   0.9475   0.0385
  -7.500  -0.4912   0.04394   0.03491  -0.0675   0.9350   0.0393
  -7.250  -0.4579   0.04120   0.03176  -0.0690   0.9244   0.0402
  -7.000  -0.4176   0.03880   0.02897  -0.0706   0.9175   0.0416
  -6.750  -0.3791   0.03708   0.02699  -0.0709   0.9084   0.0436
  -6.500  -0.3378   0.03559   0.02548  -0.0720   0.9024   0.0487
  -6.250  -0.3035   0.03460   0.02426  -0.0718   0.8922   0.0540
  -6.000  -0.2750   0.03332   0.02297  -0.0720   0.8822   0.0596
  -5.750  -0.2479   0.03199   0.02153  -0.0728   0.8726   0.0701
  -5.500  -0.2297   0.03062   0.02018  -0.0728   0.8607   0.0846
  -5.250  -0.2158   0.02878   0.01864  -0.0729   0.8495   0.1192
  -5.000  -0.2167   0.02631   0.01844  -0.0701   0.8397   0.4048
  -4.750  -0.1933   0.02987   0.02216  -0.0633   0.8309   0.5870
  -4.500  -0.1630   0.03426   0.02629  -0.0553   0.8244   0.6493
  -4.250  -0.1376   0.03471   0.02642  -0.0537   0.8162   0.6664
  -4.000  -0.1128   0.03451   0.02588  -0.0535   0.8090   0.6766
  -3.750  -0.0927   0.03421   0.02530  -0.0532   0.8010   0.6876
  -3.500  -0.0653   0.03407   0.02489  -0.0528   0.7947   0.6944
  -3.250  -0.0464   0.03383   0.02444  -0.0523   0.7869   0.7037
  -3.000  -0.0174   0.03360   0.02393  -0.0525   0.7818   0.7110
  -2.750  -0.0010   0.03349   0.02368  -0.0515   0.7738   0.7192
  -2.500   0.0258   0.03327   0.02324  -0.0517   0.7683   0.7260
  -2.250   0.0440   0.03314   0.02298  -0.0510   0.7612   0.7334
  -2.000   0.0680   0.03302   0.02268  -0.0507   0.7554   0.7394
  -1.750   0.0913   0.03281   0.02230  -0.0510   0.7499   0.7469
  -1.500   0.1103   0.03283   0.02224  -0.0498   0.7429   0.7521
  -1.250   0.1362   0.03264   0.02187  -0.0504   0.7380   0.7589
  -1.000   0.1541   0.03269   0.02185  -0.0494   0.7313   0.7640
  -0.750   0.1768   0.03265   0.02171  -0.0491   0.7255   0.7693
  -0.500   0.2057   0.03246   0.02138  -0.0502   0.7214   0.7755
  -0.250   0.2183   0.03271   0.02162  -0.0483   0.7137   0.7798
   0.000   0.2441   0.03265   0.02147  -0.0485   0.7087   0.7849
   0.250   0.2654   0.03277   0.02152  -0.0486   0.7028   0.7905
   0.500   0.2842   0.03292   0.02164  -0.0476   0.6963   0.7947
   0.750   0.3131   0.03283   0.02147  -0.0481   0.6921   0.7995
   1.000   0.3280   0.03323   0.02188  -0.0475   0.6843   0.8050
   1.250   0.3516   0.03326   0.02188  -0.0470   0.6790   0.8089
   1.500   0.3736   0.03344   0.02203  -0.0467   0.6734   0.8135
   1.750   0.3931   0.03381   0.02241  -0.0466   0.6662   0.8185
   2.000   0.4221   0.03376   0.02233  -0.0470   0.6620   0.8223
   2.250   0.4334   0.03439   0.02303  -0.0456   0.6538   0.8269
   2.500   0.4612   0.03452   0.02315  -0.0462   0.6486   0.8314
   2.750   0.4818   0.03496   0.02362  -0.0461   0.6422   0.8357
   3.000   0.5002   0.03536   0.02407  -0.0453   0.6352   0.8399
   3.250   0.5327   0.03529   0.02401  -0.0462   0.6313   0.8440
   3.500   0.5436   0.03633   0.02514  -0.0456   0.6216   0.8488
   3.750   0.5724   0.03626   0.02510  -0.0456   0.6171   0.8526
   4.000   0.5817   0.03728   0.02624  -0.0444   0.6077   0.8574
   4.250   0.6129   0.03734   0.02635  -0.0453   0.6027   0.8616
   4.500   0.6228   0.03840   0.02752  -0.0442   0.5936   0.8661
   4.750   0.6494   0.03854   0.02773  -0.0443   0.5881   0.8705
   5.000   0.6614   0.03969   0.02901  -0.0437   0.5790   0.8753
   5.250   0.6882   0.03994   0.02935  -0.0440   0.5733   0.8795
   5.500   0.6959   0.04119   0.03072  -0.0429   0.5637   0.8845
   5.750   0.7241   0.04134   0.03098  -0.0432   0.5581   0.8892
   6.000   0.7287   0.04286   0.03265  -0.0421   0.5475   0.8943
   6.250   0.7594   0.04267   0.03258  -0.0422   0.5426   0.8990
   6.500   0.7616   0.04451   0.03456  -0.0412   0.5311   0.9048
   6.750   0.7954   0.04403   0.03421  -0.0414   0.5269   0.9098
   7.000   0.7949   0.04623   0.03658  -0.0406   0.5148   0.9163
   7.250   0.8327   0.04544   0.03594  -0.0409   0.5113   0.9218
   7.500   0.8303   0.04782   0.03847  -0.0401   0.4986   0.9293
   8.000   0.8592   0.04987   0.04085  -0.0396   0.4797   0.9460
   8.250   0.8736   0.05092   0.04209  -0.0396   0.4695   0.9570
   8.750   0.9202   0.05145   0.04299  -0.0400   0.4531   0.9999
   9.250   0.9383   0.05603   0.04790  -0.0420   0.4273   0.9999
   9.750   0.9980   0.05551   0.04780  -0.0427   0.4102   0.9999
  10.000   1.0073   0.05763   0.05010  -0.0434   0.3971   0.9999
  10.250   1.0193   0.05942   0.05206  -0.0439   0.3843   0.9999
  10.500   1.0372   0.06036   0.05318  -0.0442   0.3723   0.9999
  11.000   1.1078   0.05755   0.05082  -0.0435   0.3510   0.9999
  11.250   1.1257   0.05815   0.05157  -0.0434   0.3362   0.9999
  11.500   1.1346   0.05981   0.05334  -0.0435   0.3197   0.9999
  11.750   1.1369   0.06231   0.05596  -0.0437   0.3024   0.9999
  12.000   1.1451   0.06406   0.05781  -0.0437   0.2853   0.9999
  12.250   1.1543   0.06575   0.05963  -0.0437   0.2690   0.9999
  12.500   1.1628   0.06752   0.06147  -0.0436   0.2529   0.9999
  12.750   1.1721   0.06901   0.06297  -0.0433   0.2358   0.9999
  13.000   1.1726   0.07172   0.06565  -0.0434   0.2183   0.9999
  13.250   1.1680   0.07524   0.06920  -0.0439   0.2013   0.9999
  13.500   1.1647   0.07865   0.07259  -0.0445   0.1849   0.9999
  13.750   1.1610   0.08220   0.07609  -0.0451   0.1693   0.9999
  14.000   1.1569   0.08597   0.07985  -0.0459   0.1553   0.9999
  14.250   1.1530   0.08983   0.08371  -0.0468   0.1426   0.9999
  14.500   1.1497   0.09371   0.08758  -0.0477   0.1311   0.9999
  14.750   1.1471   0.09747   0.09129  -0.0487   0.1206   0.9999
  15.000   1.1444   0.10141   0.09526  -0.0497   0.1110   0.9999
  15.250   1.1399   0.10586   0.09982  -0.0512   0.1024   0.9999
  15.500   1.1387   0.10962   0.10358  -0.0523   0.0947   0.9999
  15.750   1.1355   0.11404   0.10814  -0.0539   0.0878   0.9999
  16.000   1.1365   0.11754   0.11162  -0.0549   0.0821   0.9999
  16.250   1.1309   0.12273   0.11704  -0.0570   0.0770   0.9999
  16.500   1.1351   0.12548   0.11965  -0.0580   0.0715   0.9999
  16.750   1.1246   0.13208   0.12657  -0.0613   0.0682   0.9999
  17.000   1.1171   0.13810   0.13280  -0.0643   0.0651   0.9999
  17.250   1.1290   0.13916   0.13365  -0.0643   0.0601   0.9999
  17.500   1.1124   0.14773   0.14256  -0.0694   0.0588   0.9999
  17.750   1.0920   0.15780   0.15288  -0.0756   0.0581   0.9999
  18.000   1.0646   0.17085   0.16609  -0.0839   0.0583   0.9999
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