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FX 60-157 AIRFOIL (fx60157-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 60-157 AIRFOIL (fx60157-il)
Reynolds number: 200,000
Max Cl/Cd: 56.52 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx60157-il-200000.txt
Download as CSV file: xf-fx60157-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-157 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5369   0.09275   0.08962  -0.0468   1.0000   0.0581
 -10.000  -0.5774   0.08494   0.08180  -0.0505   1.0000   0.0576
  -9.750  -0.6136   0.07927   0.07606  -0.0524   0.9991   0.0574
  -9.500  -0.6354   0.07393   0.07058  -0.0564   0.9947   0.0578
  -9.250  -0.7406   0.05625   0.05169  -0.0563   0.9832   0.0334
  -9.000  -0.7688   0.04617   0.04042  -0.0528   0.9763   0.0269
  -8.750  -0.7559   0.04254   0.03642  -0.0527   0.9730   0.0268
  -8.500  -0.7357   0.03922   0.03267  -0.0534   0.9706   0.0268
  -8.250  -0.7190   0.03664   0.02963  -0.0526   0.9667   0.0270
  -8.000  -0.6999   0.03432   0.02714  -0.0520   0.9629   0.0276
  -7.750  -0.6742   0.03317   0.02598  -0.0526   0.9599   0.0289
  -7.500  -0.6440   0.03213   0.02465  -0.0538   0.9574   0.0316
  -7.250  -0.6105   0.03071   0.02313  -0.0555   0.9555   0.0340
  -7.000  -0.5958   0.02967   0.02202  -0.0535   0.9494   0.0364
  -6.750  -0.5702   0.02831   0.02056  -0.0533   0.9461   0.0402
  -6.500  -0.5396   0.02759   0.01977  -0.0543   0.9434   0.0445
  -6.250  -0.5068   0.02675   0.01896  -0.0558   0.9414   0.0489
  -6.000  -0.4868   0.02656   0.01866  -0.0550   0.9361   0.0537
  -5.750  -0.4645   0.02578   0.01799  -0.0547   0.9319   0.0578
  -5.500  -0.4337   0.02544   0.01756  -0.0558   0.9290   0.0626
  -5.250  -0.4010   0.02452   0.01671  -0.0574   0.9268   0.0670
  -5.000  -0.3626   0.02393   0.01611  -0.0600   0.9250   0.0730
  -4.750  -0.3502   0.02313   0.01537  -0.0581   0.9169   0.0798
  -4.500  -0.3144   0.02228   0.01461  -0.0605   0.9136   0.1016
  -4.250  -0.2684   0.01943   0.01335  -0.0677   0.9125   0.3911
  -4.000  -0.2312   0.01899   0.01384  -0.0696   0.9107   0.5835
  -3.750  -0.2107   0.01936   0.01424  -0.0680   0.9043   0.6249
  -3.500  -0.1833   0.01979   0.01463  -0.0674   0.8990   0.6521
  -3.250  -0.1465   0.02026   0.01500  -0.0685   0.8959   0.6753
  -3.000  -0.1100   0.02081   0.01550  -0.0690   0.8936   0.6882
  -2.750  -0.1001   0.02122   0.01587  -0.0654   0.8839   0.6977
  -2.500  -0.0671   0.02164   0.01622  -0.0657   0.8805   0.7111
  -2.250  -0.0390   0.02233   0.01694  -0.0637   0.8779   0.7205
  -2.000  -0.0318   0.02287   0.01747  -0.0593   0.8680   0.7307
  -1.750   0.0008   0.02317   0.01772  -0.0593   0.8645   0.7434
  -1.500   0.0284   0.02346   0.01801  -0.0572   0.8621   0.7491
  -1.250   0.0455   0.02362   0.01811  -0.0559   0.8523   0.7594
  -1.000   0.0706   0.02364   0.01813  -0.0539   0.8487   0.7637
  -0.750   0.1090   0.02338   0.01782  -0.0552   0.8467   0.7688
  -0.500   0.1324   0.02332   0.01771  -0.0554   0.8374   0.7761
  -0.250   0.1622   0.02304   0.01741  -0.0549   0.8337   0.7790
   0.000   0.2002   0.02261   0.01696  -0.0563   0.8316   0.7822
   0.250   0.2350   0.02223   0.01654  -0.0576   0.8272   0.7861
   0.500   0.2719   0.02182   0.01609  -0.0600   0.8197   0.7916
   0.750   0.3089   0.02109   0.01535  -0.0607   0.8171   0.7940
   1.000   0.3493   0.02039   0.01465  -0.0621   0.8154   0.7971
   1.250   0.3940   0.01979   0.01404  -0.0647   0.8141   0.8011
   1.500   0.4144   0.01968   0.01394  -0.0640   0.8030   0.8068
   1.750   0.4596   0.01897   0.01322  -0.0669   0.8005   0.8091
   2.000   0.5092   0.01822   0.01249  -0.0703   0.7981   0.8109
   2.250   0.5237   0.01793   0.01222  -0.0674   0.7861   0.8142
   2.500   0.5778   0.01727   0.01155  -0.0722   0.7822   0.8163
   2.750   0.5994   0.01700   0.01130  -0.0712   0.7697   0.8197
   3.000   0.6389   0.01665   0.01096  -0.0738   0.7598   0.8230
   3.250   0.6776   0.01622   0.01053  -0.0755   0.7499   0.8255
   3.500   0.6961   0.01596   0.01028  -0.0732   0.7350   0.8287
   3.750   0.7235   0.01570   0.01001  -0.0729   0.7183   0.8324
   4.000   0.7527   0.01553   0.00981  -0.0732   0.6994   0.8361
   4.250   0.7819   0.01544   0.00968  -0.0738   0.6774   0.8389
   4.500   0.8096   0.01534   0.00950  -0.0739   0.6543   0.8408
   4.750   0.8277   0.01530   0.00940  -0.0719   0.6288   0.8428
   5.000   0.8496   0.01537   0.00935  -0.0708   0.6018   0.8449
   5.250   0.8669   0.01552   0.00940  -0.0690   0.5732   0.8477
   5.500   0.8865   0.01575   0.00952  -0.0677   0.5455   0.8507
   5.750   0.9077   0.01606   0.00971  -0.0670   0.5178   0.8533
   6.000   0.9270   0.01648   0.00997  -0.0661   0.4867   0.8557
   6.250   0.9397   0.01678   0.01020  -0.0635   0.4595   0.8578
   6.500   0.9522   0.01718   0.01049  -0.0611   0.4308   0.8602
   6.750   0.9660   0.01765   0.01085  -0.0591   0.4047   0.8627
   7.000   0.9818   0.01812   0.01125  -0.0576   0.3781   0.8656
   7.250   0.9982   0.01870   0.01170  -0.0563   0.3539   0.8686
   7.500   1.0184   0.01927   0.01221  -0.0559   0.3317   0.8711
   7.750   1.0322   0.01972   0.01265  -0.0540   0.3116   0.8733
   8.000   1.0468   0.02024   0.01312  -0.0523   0.2944   0.8760
   8.250   1.0625   0.02079   0.01366  -0.0509   0.2784   0.8790
   8.500   1.0802   0.02138   0.01424  -0.0500   0.2623   0.8819
   8.750   1.0984   0.02203   0.01487  -0.0493   0.2464   0.8845
   9.000   1.1169   0.02272   0.01555  -0.0488   0.2325   0.8869
   9.250   1.1295   0.02333   0.01616  -0.0469   0.2210   0.8898
   9.500   1.1436   0.02399   0.01685  -0.0454   0.2088   0.8930
   9.750   1.1607   0.02463   0.01755  -0.0445   0.1968   0.8960
  10.000   1.1774   0.02541   0.01835  -0.0438   0.1859   0.8988
  10.250   1.1932   0.02635   0.01928  -0.0431   0.1759   0.9016
  10.500   1.2064   0.02709   0.02010  -0.0417   0.1650   0.9044
  10.750   1.2200   0.02786   0.02093  -0.0404   0.1533   0.9077
  11.000   1.2326   0.02880   0.02190  -0.0393   0.1414   0.9112
  11.250   1.2444   0.02993   0.02302  -0.0383   0.1309   0.9151
  11.500   1.2545   0.03107   0.02419  -0.0369   0.1197   0.9190
  11.750   1.2646   0.03211   0.02531  -0.0355   0.1061   0.9234
  12.000   1.2702   0.03369   0.02683  -0.0340   0.0929   0.9277
  12.250   1.2759   0.03545   0.02861  -0.0327   0.0783   0.9320
  12.500   1.2770   0.03724   0.03038  -0.0307   0.0644   0.9373
  12.750   1.2748   0.03959   0.03270  -0.0290   0.0574   0.9431
  13.000   1.2728   0.04181   0.03500  -0.0272   0.0527   0.9503
  13.250   1.2658   0.04459   0.03783  -0.0255   0.0498   0.9603
  13.500   1.2678   0.04653   0.03994  -0.0245   0.0475   0.9985
  13.750   1.2749   0.04917   0.04271  -0.0250   0.0453   1.0000
  14.000   1.2802   0.05199   0.04562  -0.0255   0.0437   1.0000
  14.250   1.2834   0.05508   0.04877  -0.0261   0.0425   1.0000
  14.500   1.2866   0.05823   0.05198  -0.0266   0.0415   1.0000
  14.750   1.2941   0.06102   0.05491  -0.0274   0.0405   1.0000
  15.000   1.3008   0.06392   0.05793  -0.0283   0.0395   1.0000
  15.250   1.3071   0.06689   0.06102  -0.0292   0.0386   1.0000
  15.500   1.3124   0.07002   0.06424  -0.0303   0.0376   1.0000
  15.750   1.3170   0.07327   0.06756  -0.0316   0.0366   1.0000
  16.000   1.3216   0.07645   0.07077  -0.0326   0.0357   1.0000
  16.250   1.3280   0.07939   0.07376  -0.0333   0.0349   1.0000
  16.500   1.3320   0.08285   0.07739  -0.0346   0.0344   1.0000
  16.750   1.3357   0.08635   0.08105  -0.0360   0.0339   1.0000
  17.000   1.3388   0.08993   0.08478  -0.0374   0.0334   1.0000
  17.250   1.3410   0.09368   0.08869  -0.0389   0.0330   1.0000
  17.500   1.3420   0.09764   0.09281  -0.0407   0.0326   1.0000
  17.750   1.3420   0.10178   0.09710  -0.0426   0.0322   1.0000
  18.000   1.3414   0.10603   0.10148  -0.0447   0.0317   1.0000
  18.250   1.3407   0.11030   0.10588  -0.0470   0.0313   1.0000
  18.500   1.3406   0.11444   0.11011  -0.0493   0.0307   1.0000
  18.750   1.3447   0.11771   0.11339  -0.0510   0.0299   1.0000
  19.000   1.3407   0.12249   0.11829  -0.0535   0.0292   1.0000
  19.250   1.3299   0.12883   0.12486  -0.0576   0.0291   1.0000
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