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FX 60-157 AIRFOIL (fx60157-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 60-157 AIRFOIL (fx60157-il)
Reynolds number: 50,000
Max Cl/Cd: 28.59 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx60157-il-50000-n5.txt
Download as CSV file: xf-fx60157-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4903   0.10576   0.09865  -0.0585   1.0000   0.0457
 -11.500  -0.5072   0.10006   0.09299  -0.0602   1.0000   0.0455
 -11.250  -0.5251   0.09492   0.08788  -0.0614   1.0000   0.0451
 -11.000  -0.5491   0.08969   0.08265  -0.0624   1.0000   0.0448
 -10.750  -0.5736   0.08522   0.07816  -0.0626   1.0000   0.0445
 -10.500  -0.5998   0.08124   0.07415  -0.0619   1.0000   0.0442
 -10.250  -0.6277   0.07775   0.07060  -0.0603   1.0000   0.0439
 -10.000  -0.6554   0.07491   0.06770  -0.0578   1.0000   0.0437
  -9.750  -0.6824   0.07253   0.06528  -0.0543   1.0000   0.0433
  -9.500  -0.7097   0.07014   0.06278  -0.0506   1.0000   0.0432
  -9.250  -0.7295   0.06737   0.05983  -0.0475   1.0000   0.0432
  -9.000  -0.7458   0.06434   0.05657  -0.0446   1.0000   0.0436
  -8.500  -0.7637   0.05796   0.04949  -0.0394   1.0000   0.0446
  -8.250  -0.7649   0.05478   0.04586  -0.0372   1.0000   0.0453
  -8.000  -0.7593   0.05220   0.04304  -0.0355   1.0000   0.0466
  -7.750  -0.7494   0.05045   0.04124  -0.0341   1.0000   0.0490
  -7.500  -0.7395   0.04820   0.03862  -0.0326   1.0000   0.0517
  -7.250  -0.7277   0.04601   0.03606  -0.0312   1.0000   0.0550
  -7.000  -0.7130   0.04443   0.03441  -0.0300   1.0000   0.0583
  -6.750  -0.6911   0.04263   0.03208  -0.0297   0.9982   0.0630
  -6.500  -0.6641   0.04100   0.03043  -0.0300   0.9952   0.0666
  -6.250  -0.6361   0.03971   0.02898  -0.0299   0.9923   0.0706
  -6.000  -0.6090   0.03865   0.02777  -0.0295   0.9889   0.0759
  -5.750  -0.5812   0.03788   0.02696  -0.0293   0.9854   0.0810
  -5.500  -0.5523   0.03725   0.02618  -0.0290   0.9821   0.0865
  -5.250  -0.5306   0.03641   0.02534  -0.0285   0.9777   0.0942
  -5.000  -0.5072   0.03556   0.02447  -0.0285   0.9732   0.1047
  -4.750  -0.4818   0.03465   0.02360  -0.0292   0.9694   0.1197
  -4.500  -0.4633   0.03343   0.02260  -0.0290   0.9643   0.1484
  -4.250  -0.4438   0.03130   0.02140  -0.0303   0.9598   0.2486
  -4.000  -0.4323   0.03083   0.02272  -0.0261   0.9556   0.4986
  -3.750  -0.4178   0.03207   0.02408  -0.0211   0.9490   0.5846
  -3.250  -0.3720   0.03469   0.02627  -0.0167   0.9368   0.6877
  -3.000  -0.3566   0.03622   0.02766  -0.0117   0.9299   0.7227
  -2.750  -0.3330   0.03759   0.02888  -0.0083   0.9250   0.7503
  -2.500  -0.3185   0.03783   0.02895  -0.0052   0.9176   0.7668
  -2.250  -0.2923   0.03792   0.02882  -0.0051   0.9120   0.7796
  -2.000  -0.2696   0.03782   0.02852  -0.0048   0.9055   0.7912
  -1.750  -0.2449   0.03777   0.02830  -0.0043   0.8984   0.7987
  -1.500  -0.2126   0.03766   0.02796  -0.0061   0.8929   0.8079
  -1.250  -0.1949   0.03749   0.02767  -0.0044   0.8841   0.8145
  -1.000  -0.1639   0.03740   0.02740  -0.0058   0.8783   0.8236
  -0.750  -0.1457   0.03728   0.02718  -0.0043   0.8699   0.8303
  -0.500  -0.1170   0.03719   0.02694  -0.0052   0.8636   0.8384
  -0.250  -0.0962   0.03707   0.02674  -0.0044   0.8553   0.8449
   0.000  -0.0678   0.03697   0.02653  -0.0050   0.8482   0.8525
   0.250  -0.0463   0.03682   0.02631  -0.0044   0.8391   0.8594
   0.500  -0.0156   0.03668   0.02608  -0.0053   0.8318   0.8653
   0.750   0.0036   0.03654   0.02586  -0.0047   0.8220   0.8712
   1.000   0.0367   0.03640   0.02566  -0.0060   0.8154   0.8751
   1.250   0.0556   0.03633   0.02556  -0.0052   0.8053   0.8802
   1.500   0.0893   0.03618   0.02533  -0.0068   0.7988   0.8849
   1.750   0.1081   0.03609   0.02523  -0.0059   0.7874   0.8899
   2.000   0.1433   0.03584   0.02496  -0.0073   0.7803   0.8943
   2.250   0.1643   0.03574   0.02484  -0.0068   0.7688   0.8993
   2.500   0.1872   0.03566   0.02476  -0.0066   0.7579   0.9035
   2.750   0.2228   0.03538   0.02449  -0.0081   0.7507   0.9067
   3.000   0.2432   0.03536   0.02449  -0.0076   0.7383   0.9111
   3.250   0.2704   0.03518   0.02432  -0.0079   0.7278   0.9153
   3.500   0.3047   0.03478   0.02396  -0.0089   0.7188   0.9187
   3.750   0.3275   0.03473   0.02396  -0.0086   0.7058   0.9225
   4.000   0.3554   0.03455   0.02382  -0.0090   0.6950   0.9265
   4.250   0.3901   0.03404   0.02337  -0.0099   0.6862   0.9305
   4.500   0.4151   0.03388   0.02330  -0.0098   0.6728   0.9347
   4.750   0.4437   0.03357   0.02306  -0.0100   0.6603   0.9389
   5.000   0.4846   0.03270   0.02226  -0.0114   0.6523   0.9427
   5.250   0.5104   0.03257   0.02224  -0.0113   0.6379   0.9474
   5.500   0.5398   0.03233   0.02210  -0.0118   0.6239   0.9519
   5.750   0.5718   0.03194   0.02180  -0.0124   0.6100   0.9567
   6.000   0.6068   0.03144   0.02141  -0.0133   0.5953   0.9612
   6.250   0.6423   0.03098   0.02104  -0.0143   0.5792   0.9660
   6.500   0.6769   0.03063   0.02078  -0.0153   0.5623   0.9715
   6.750   0.7138   0.03032   0.02056  -0.0167   0.5448   0.9768
   7.000   0.7486   0.03008   0.02039  -0.0178   0.5258   0.9837
   7.250   0.7799   0.02983   0.02018  -0.0184   0.5059   0.9972
   7.500   0.8070   0.02986   0.02019  -0.0184   0.4849   1.0000
   7.750   0.8289   0.03025   0.02061  -0.0181   0.4630   1.0000
   8.000   0.8529   0.03069   0.02108  -0.0182   0.4422   1.0000
   8.250   0.8788   0.03114   0.02153  -0.0184   0.4227   1.0000
   8.500   0.9049   0.03165   0.02203  -0.0188   0.4037   1.0000
   8.750   0.9249   0.03248   0.02292  -0.0187   0.3842   1.0000
   9.000   0.9441   0.03334   0.02383  -0.0185   0.3647   1.0000
   9.250   0.9639   0.03422   0.02473  -0.0184   0.3460   1.0000
   9.500   0.9841   0.03518   0.02575  -0.0184   0.3288   1.0000
   9.750   1.0048   0.03621   0.02685  -0.0185   0.3129   1.0000
  10.000   1.0266   0.03726   0.02797  -0.0188   0.2987   1.0000
  10.250   1.0488   0.03833   0.02910  -0.0190   0.2849   1.0000
  10.500   1.0685   0.03947   0.03029  -0.0191   0.2708   1.0000
  10.750   1.0830   0.04081   0.03174  -0.0187   0.2567   1.0000
  11.000   1.0941   0.04233   0.03338  -0.0182   0.2431   1.0000
  11.250   1.1058   0.04390   0.03507  -0.0178   0.2305   1.0000
  11.500   1.1199   0.04544   0.03672  -0.0175   0.2191   1.0000
  11.750   1.1342   0.04692   0.03822  -0.0173   0.2080   1.0000
  12.000   1.1387   0.04906   0.04061  -0.0167   0.1969   1.0000
  12.250   1.1436   0.05112   0.04280  -0.0161   0.1862   1.0000
  12.500   1.1484   0.05309   0.04477  -0.0157   0.1758   1.0000
  12.750   1.1471   0.05575   0.04761  -0.0153   0.1653   1.0000
  13.000   1.1455   0.05860   0.05065  -0.0151   0.1556   1.0000
  13.250   1.1463   0.06119   0.05326  -0.0151   0.1468   1.0000
  13.500   1.1436   0.06456   0.05688  -0.0153   0.1383   1.0000
  13.750   1.1439   0.06754   0.05990  -0.0157   0.1308   1.0000
  14.000   1.1387   0.07143   0.06400  -0.0164   0.1230   1.0000
  14.250   1.1350   0.07519   0.06782  -0.0173   0.1159   1.0000
  14.500   1.1269   0.07982   0.07268  -0.0188   0.1090   1.0000
  14.750   1.1218   0.08409   0.07702  -0.0203   0.1029   1.0000
  15.000   1.1131   0.08923   0.08236  -0.0224   0.0973   1.0000
  15.250   1.1145   0.09257   0.08560  -0.0238   0.0922   1.0000
  15.500   1.0992   0.09942   0.09281  -0.0269   0.0882   1.0000
  15.750   1.0886   0.10549   0.09906  -0.0299   0.0843   1.0000
  16.000   1.0952   0.10811   0.10159  -0.0310   0.0800   1.0000
  16.250   1.0720   0.11725   0.11106  -0.0360   0.0780   1.0000
  16.500   1.0400   0.12884   0.12294  -0.0428   0.0766   1.0000
  16.750   0.9860   0.14711   0.14138  -0.0538   0.0758   1.0000
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