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FX 60-160 AIRFOIL (fx60160-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 60-160 AIRFOIL (fx60160-il)
Reynolds number: 100,000
Max Cl/Cd: 51.02 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx60160-il-100000.txt
Download as CSV file: xf-fx60160-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-160 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3652   0.11544   0.11055  -0.0468   1.0000   0.1433
 -10.500  -0.3982   0.11331   0.10857  -0.0479   1.0000   0.1493
 -10.250  -0.4595   0.11128   0.10679  -0.0496   1.0000   0.1504
 -10.000  -0.3911   0.10869   0.10404  -0.0425   1.0000   0.1577
  -9.750  -0.4096   0.10711   0.10256  -0.0406   1.0000   0.1628
  -9.500  -0.4629   0.10554   0.10120  -0.0403   1.0000   0.1658
  -9.250  -0.4481   0.10329   0.09896  -0.0362   1.0000   0.1704
  -9.000  -0.4496   0.10227   0.09797  -0.0330   1.0000   0.1761
  -8.750  -0.4902   0.10024   0.09609  -0.0323   1.0000   0.1809
  -8.500  -0.4733   0.09726   0.09310  -0.0319   0.9978   0.1886
  -8.250  -0.4817   0.09215   0.08803  -0.0382   0.9911   0.2015
  -7.000  -0.5588   0.04853   0.04178  -0.0706   0.9438   0.1025
  -6.750  -0.5293   0.04462   0.03752  -0.0729   0.9404   0.0996
  -6.500  -0.5148   0.04227   0.03483  -0.0718   0.9338   0.0986
  -6.250  -0.4873   0.03952   0.03160  -0.0727   0.9289   0.0961
  -6.000  -0.4516   0.03718   0.02877  -0.0746   0.9255   0.0951
  -5.750  -0.4327   0.03597   0.02736  -0.0736   0.9194   0.0965
  -5.500  -0.4048   0.03474   0.02588  -0.0741   0.9143   0.0988
  -5.250  -0.3678   0.03337   0.02426  -0.0758   0.9108   0.1003
  -5.000  -0.3445   0.03252   0.02324  -0.0751   0.9053   0.1019
  -4.750  -0.3189   0.03176   0.02233  -0.0750   0.8999   0.1051
  -4.500  -0.2845   0.03065   0.02135  -0.0764   0.8962   0.1099
  -4.250  -0.2592   0.03009   0.02080  -0.0761   0.8911   0.1138
  -4.000  -0.2381   0.02972   0.02038  -0.0751   0.8850   0.1184
  -3.750  -0.2060   0.02895   0.01980  -0.0762   0.8811   0.1279
  -3.500  -0.1834   0.02856   0.01944  -0.0757   0.8756   0.1376
  -3.250  -0.1626   0.02816   0.01907  -0.0750   0.8694   0.1519
  -3.000  -0.1350   0.02579   0.01812  -0.0769   0.8657   0.3728
  -2.750  -0.1295   0.02693   0.02021  -0.0708   0.8586   0.6142
  -2.500  -0.1092   0.02822   0.02139  -0.0679   0.8524   0.6568
  -2.250  -0.0785   0.02921   0.02235  -0.0662   0.8487   0.6822
  -2.000  -0.0762   0.03005   0.02317  -0.0614   0.8399   0.6990
  -1.750  -0.0521   0.03068   0.02374  -0.0591   0.8351   0.7231
  -1.500  -0.0386   0.03122   0.02425  -0.0557   0.8287   0.7400
  -1.250  -0.0257   0.03159   0.02461  -0.0523   0.8218   0.7570
  -1.000   0.0006   0.03170   0.02466  -0.0503   0.8179   0.7780
  -0.750   0.0022   0.03208   0.02503  -0.0461   0.8089   0.7914
  -0.500   0.0278   0.03200   0.02487  -0.0452   0.8039   0.8054
  -0.250   0.0707   0.03169   0.02443  -0.0477   0.8010   0.8156
   0.000   0.0679   0.03215   0.02488  -0.0435   0.7903   0.8231
   0.250   0.1067   0.03187   0.02450  -0.0455   0.7865   0.8317
   0.500   0.1119   0.03228   0.02490  -0.0425   0.7771   0.8405
   0.750   0.1422   0.03208   0.02464  -0.0429   0.7720   0.8497
   1.000   0.1844   0.03169   0.02418  -0.0450   0.7692   0.8587
   1.250   0.1825   0.03233   0.02483  -0.0413   0.7577   0.8662
   1.500   0.2239   0.03198   0.02442  -0.0435   0.7543   0.8732
   1.750   0.2292   0.03261   0.02506  -0.0410   0.7436   0.8802
   2.000   0.2670   0.03233   0.02474  -0.0427   0.7393   0.8868
   2.250   0.3081   0.03199   0.02438  -0.0447   0.7359   0.8931
   2.500   0.3130   0.03277   0.02517  -0.0424   0.7245   0.9007
   2.750   0.3586   0.03227   0.02466  -0.0450   0.7218   0.9069
   3.000   0.3618   0.03330   0.02573  -0.0427   0.7097   0.9154
   3.250   0.4072   0.03280   0.02524  -0.0452   0.7067   0.9222
   3.500   0.4563   0.03216   0.02464  -0.0482   0.7045   0.9288
   3.750   0.4643   0.03343   0.02598  -0.0471   0.6916   0.9396
   4.000   0.4882   0.03443   0.02705  -0.0484   0.6817   0.9508
   4.250   0.5377   0.03425   0.02695  -0.0523   0.6770   0.9616
   4.500   0.5967   0.03346   0.02624  -0.0570   0.6749   0.9749
   4.750   0.6569   0.03237   0.02523  -0.0615   0.6735   1.0000
   5.000   0.6497   0.03438   0.02726  -0.0588   0.6595   1.0000
   5.250   0.6537   0.03616   0.02907  -0.0576   0.6470   1.0000
   5.500   0.7008   0.03539   0.02837  -0.0600   0.6442   1.0000
   5.750   0.7543   0.03428   0.02735  -0.0631   0.6427   1.0000
   6.000   0.8177   0.03257   0.02575  -0.0672   0.6408   1.0000
   6.250   0.8255   0.03353   0.02677  -0.0653   0.6279   1.0000
   6.750   0.9958   0.02589   0.01933  -0.0768   0.6115   1.0000
   7.000   1.0291   0.02496   0.01846  -0.0770   0.5973   1.0000
   7.250   1.0618   0.02413   0.01771  -0.0771   0.5827   1.0000
   7.500   1.0947   0.02320   0.01682  -0.0772   0.5660   1.0000
   7.750   1.1223   0.02250   0.01614  -0.0764   0.5468   1.0000
   8.000   1.1297   0.02249   0.01621  -0.0728   0.5255   1.0000
   8.250   1.1383   0.02231   0.01598  -0.0691   0.4972   1.0000
   8.500   1.1415   0.02258   0.01620  -0.0650   0.4646   1.0000
   8.750   1.1388   0.02326   0.01668  -0.0602   0.4201   1.0000
   9.000   1.1271   0.02466   0.01773  -0.0549   0.3551   1.0000
   9.250   1.1062   0.02705   0.01951  -0.0493   0.2632   1.0000
   9.500   1.0827   0.03026   0.02205  -0.0447   0.1896   1.0000
   9.750   1.0705   0.03315   0.02458  -0.0416   0.1559   1.0000
  10.000   1.0662   0.03561   0.02688  -0.0393   0.1405   1.0000
  10.250   1.0671   0.03776   0.02898  -0.0376   0.1313   1.0000
  10.500   1.0689   0.03986   0.03102  -0.0359   0.1250   1.0000
  10.750   1.0774   0.04149   0.03266  -0.0346   0.1195   1.0000
  11.000   1.0885   0.04295   0.03409  -0.0334   0.1143   1.0000
  11.250   1.1085   0.04396   0.03492  -0.0324   0.1096   1.0000
  11.500   1.1346   0.04471   0.03574  -0.0318   0.1060   1.0000
  11.750   1.1680   0.04536   0.03637  -0.0316   0.1025   1.0000
  12.000   1.2343   0.04606   0.03680  -0.0341   0.0968   1.0000
  12.250   1.2636   0.04752   0.03852  -0.0341   0.0945   1.0000
  12.500   1.2906   0.04926   0.04045  -0.0342   0.0908   1.0000
  12.750   1.3347   0.05213   0.04322  -0.0365   0.0832   1.0000
  13.000   1.3299   0.05391   0.04532  -0.0338   0.0807   1.0000
  13.250   1.3363   0.05606   0.04770  -0.0324   0.0771   1.0000
  13.500   1.3749   0.06042   0.05206  -0.0345   0.0707   1.0000
  13.750   1.3583   0.06252   0.05452  -0.0310   0.0694   1.0000
  14.000   1.3458   0.06527   0.05761  -0.0285   0.0677   1.0000
  14.250   1.3357   0.06840   0.06104  -0.0266   0.0656   1.0000
  14.500   1.3366   0.07150   0.06429  -0.0256   0.0629   1.0000
  14.750   1.3588   0.07774   0.07054  -0.0266   0.0593   1.0000
  15.000   1.3353   0.08125   0.07436  -0.0246   0.0590   1.0000
  15.250   1.3113   0.08519   0.07860  -0.0233   0.0588   1.0000
  15.500   1.2875   0.08980   0.08349  -0.0228   0.0586   1.0000
  15.750   1.2620   0.09478   0.08875  -0.0228   0.0585   1.0000
  16.000   1.2363   0.10029   0.09452  -0.0236   0.0584   1.0000
  16.250   1.2114   0.10635   0.10080  -0.0251   0.0586   1.0000
  16.500   1.1863   0.11287   0.10754  -0.0274   0.0587   1.0000
  16.750   1.1627   0.11990   0.11474  -0.0302   0.0590   1.0000
  17.000   1.1396   0.12757   0.12256  -0.0336   0.0593   1.0000
  17.250   1.0147   0.15563   0.15108  -0.0537   0.0702   1.0000
  17.500   1.0129   0.16282   0.15827  -0.0561   0.0711   1.0000
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