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FX 60-157 AIRFOIL (fx60157-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 60-157 AIRFOIL (fx60157-il)
Reynolds number: 100,000
Max Cl/Cd: 41.87 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx60157-il-100000-n5.txt
Download as CSV file: xf-fx60157-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.5420   0.09204   0.08692  -0.0616   1.0000   0.0226
 -12.000  -0.5675   0.08552   0.08036  -0.0641   1.0000   0.0224
 -11.750  -0.5907   0.08045   0.07524  -0.0653   1.0000   0.0222
 -11.500  -0.6153   0.07591   0.07064  -0.0657   1.0000   0.0220
 -11.250  -0.6413   0.07188   0.06652  -0.0652   1.0000   0.0218
 -11.000  -0.6694   0.06814   0.06267  -0.0638   1.0000   0.0217
 -10.750  -0.6889   0.06352   0.05782  -0.0651   0.9969   0.0217
 -10.500  -0.7069   0.05907   0.05304  -0.0663   0.9918   0.0219
 -10.250  -0.7258   0.05551   0.04913  -0.0655   0.9859   0.0222
 -10.000  -0.7351   0.05199   0.04521  -0.0650   0.9806   0.0224
  -9.750  -0.7375   0.04870   0.04150  -0.0639   0.9748   0.0228
  -9.500  -0.7247   0.04665   0.03930  -0.0641   0.9714   0.0233
  -9.250  -0.7120   0.04449   0.03690  -0.0638   0.9678   0.0239
  -9.000  -0.7015   0.04246   0.03464  -0.0626   0.9630   0.0246
  -8.750  -0.6847   0.04018   0.03202  -0.0623   0.9595   0.0257
  -8.500  -0.6627   0.03781   0.02924  -0.0623   0.9570   0.0273
  -8.250  -0.6407   0.03661   0.02798  -0.0625   0.9541   0.0285
  -8.000  -0.6262   0.03551   0.02672  -0.0609   0.9495   0.0306
  -7.750  -0.6055   0.03441   0.02547  -0.0606   0.9460   0.0337
  -7.500  -0.5802   0.03339   0.02426  -0.0609   0.9432   0.0371
  -7.250  -0.5530   0.03248   0.02331  -0.0618   0.9410   0.0412
  -7.000  -0.5374   0.03189   0.02253  -0.0603   0.9363   0.0458
  -6.750  -0.5184   0.03105   0.02178  -0.0595   0.9324   0.0489
  -6.500  -0.4938   0.03019   0.02085  -0.0594   0.9293   0.0515
  -6.250  -0.4668   0.02935   0.01994  -0.0597   0.9268   0.0545
  -6.000  -0.4416   0.02860   0.01920  -0.0600   0.9239   0.0587
  -5.750  -0.4277   0.02801   0.01853  -0.0580   0.9180   0.0624
  -5.500  -0.4035   0.02718   0.01767  -0.0582   0.9140   0.0671
  -5.250  -0.3744   0.02646   0.01689  -0.0592   0.9112   0.0749
  -5.000  -0.3436   0.02571   0.01620  -0.0606   0.9090   0.0871
  -4.750  -0.3309   0.02520   0.01575  -0.0586   0.9023   0.1044
  -4.500  -0.3056   0.02423   0.01517  -0.0593   0.8986   0.1634
  -4.250  -0.2772   0.02254   0.01453  -0.0617   0.8961   0.3625
  -4.000  -0.2520   0.02217   0.01508  -0.0609   0.8938   0.5200
  -3.750  -0.2421   0.02275   0.01588  -0.0564   0.8865   0.5833
  -3.500  -0.2131   0.02314   0.01618  -0.0562   0.8820   0.6278
  -3.250  -0.1815   0.02364   0.01656  -0.0561   0.8788   0.6530
  -3.000  -0.1600   0.02415   0.01695  -0.0546   0.8727   0.6775
  -2.750  -0.1411   0.02490   0.01767  -0.0517   0.8670   0.6955
  -2.500  -0.1135   0.02544   0.01811  -0.0506   0.8635   0.7113
  -2.250  -0.0966   0.02582   0.01844  -0.0477   0.8570   0.7187
  -2.000  -0.0673   0.02571   0.01819  -0.0485   0.8512   0.7276
  -1.750  -0.0367   0.02568   0.01807  -0.0485   0.8475   0.7317
  -1.500  -0.0128   0.02569   0.01799  -0.0479   0.8417   0.7376
  -1.250   0.0149   0.02559   0.01779  -0.0486   0.8356   0.7440
  -1.000   0.0451   0.02550   0.01762  -0.0486   0.8320   0.7475
  -0.750   0.0711   0.02543   0.01750  -0.0484   0.8262   0.7523
  -0.500   0.1006   0.02527   0.01725  -0.0494   0.8191   0.7585
  -0.250   0.1334   0.02501   0.01694  -0.0499   0.8154   0.7618
   0.000   0.1516   0.02508   0.01700  -0.0482   0.8070   0.7660
   0.250   0.1822   0.02491   0.01679  -0.0488   0.8019   0.7712
   0.500   0.2220   0.02451   0.01632  -0.0512   0.7989   0.7760
   0.750   0.2380   0.02456   0.01638  -0.0490   0.7886   0.7792
   1.000   0.2712   0.02416   0.01597  -0.0497   0.7842   0.7826
   1.500   0.3315   0.02367   0.01545  -0.0509   0.7695   0.7905
   1.750   0.3703   0.02309   0.01486  -0.0525   0.7657   0.7932
   2.000   0.3871   0.02308   0.01488  -0.0505   0.7535   0.7963
   2.250   0.4160   0.02276   0.01457  -0.0505   0.7450   0.7996
   2.500   0.4473   0.02243   0.01427  -0.0511   0.7363   0.8031
   2.750   0.4772   0.02225   0.01410  -0.0518   0.7258   0.8065
   3.000   0.5152   0.02174   0.01359  -0.0534   0.7180   0.8086
   3.250   0.5381   0.02161   0.01351  -0.0525   0.7043   0.8107
   3.500   0.5654   0.02138   0.01332  -0.0523   0.6909   0.8130
   3.750   0.5964   0.02109   0.01304  -0.0527   0.6771   0.8156
   4.000   0.6295   0.02080   0.01277  -0.0535   0.6618   0.8183
   4.250   0.6628   0.02060   0.01256  -0.0546   0.6451   0.8208
   4.500   0.6972   0.02042   0.01237  -0.0559   0.6265   0.8231
   4.750   0.7301   0.02024   0.01217  -0.0567   0.6069   0.8249
   5.000   0.7605   0.02014   0.01202  -0.0570   0.5862   0.8268
   5.250   0.7844   0.02024   0.01209  -0.0564   0.5622   0.8294
   5.500   0.8121   0.02033   0.01210  -0.0564   0.5376   0.8320
   5.750   0.8362   0.02057   0.01229  -0.0560   0.5131   0.8348
   6.000   0.8616   0.02086   0.01251  -0.0560   0.4889   0.8374
   6.250   0.8855   0.02122   0.01281  -0.0558   0.4652   0.8401
   6.500   0.9026   0.02157   0.01313  -0.0541   0.4423   0.8426
   6.750   0.9204   0.02198   0.01348  -0.0527   0.4198   0.8454
   7.000   0.9388   0.02245   0.01392  -0.0515   0.3974   0.8483
   7.250   0.9579   0.02296   0.01441  -0.0507   0.3757   0.8510
   7.500   0.9775   0.02354   0.01493  -0.0500   0.3561   0.8540
   7.750   0.9947   0.02412   0.01547  -0.0488   0.3380   0.8569
   8.000   1.0100   0.02468   0.01605  -0.0472   0.3202   0.8597
   8.250   1.0259   0.02530   0.01668  -0.0459   0.3027   0.8626
   8.500   1.0420   0.02600   0.01736  -0.0448   0.2859   0.8655
   8.750   1.0581   0.02675   0.01812  -0.0438   0.2684   0.8684
   9.000   1.0742   0.02756   0.01893  -0.0429   0.2505   0.8713
   9.250   1.0855   0.02833   0.01970  -0.0411   0.2352   0.8744
   9.500   1.0976   0.02918   0.02054  -0.0395   0.2217   0.8779
   9.750   1.1111   0.03006   0.02146  -0.0383   0.2080   0.8816
  10.000   1.1258   0.03097   0.02245  -0.0374   0.1942   0.8852
  10.250   1.1382   0.03192   0.02344  -0.0361   0.1824   0.8885
  10.500   1.1493   0.03290   0.02448  -0.0347   0.1719   0.8921
  10.750   1.1598   0.03401   0.02563  -0.0334   0.1612   0.8959
  11.000   1.1733   0.03506   0.02682  -0.0325   0.1497   0.8999
  11.250   1.1834   0.03621   0.02806  -0.0313   0.1404   0.9042
  11.500   1.1897   0.03753   0.02941  -0.0297   0.1323   0.9093
  11.750   1.1996   0.03881   0.03081  -0.0285   0.1231   0.9149
  12.000   1.2062   0.04018   0.03229  -0.0271   0.1154   0.9211
  12.250   1.2127   0.04162   0.03388  -0.0258   0.1061   0.9282
  12.500   1.2168   0.04328   0.03561  -0.0245   0.0975   0.9367
  12.750   1.2186   0.04519   0.03758  -0.0233   0.0902   0.9484
  13.000   1.2192   0.04704   0.03956  -0.0221   0.0829   0.9811
  13.250   1.2261   0.04939   0.04206  -0.0224   0.0749   1.0000
  13.500   1.2301   0.05211   0.04488  -0.0226   0.0673   1.0000
  13.750   1.2314   0.05518   0.04802  -0.0230   0.0621   1.0000
  14.000   1.2293   0.05873   0.05163  -0.0236   0.0581   1.0000
  14.250   1.2288   0.06226   0.05531  -0.0243   0.0544   1.0000
  14.500   1.2249   0.06628   0.05945  -0.0253   0.0516   1.0000
  14.750   1.2183   0.07080   0.06403  -0.0266   0.0496   1.0000
  15.000   1.2173   0.07477   0.06822  -0.0279   0.0471   1.0000
  15.250   1.2140   0.07914   0.07276  -0.0294   0.0451   1.0000
  15.500   1.2093   0.08382   0.07759  -0.0313   0.0435   1.0000
  15.750   1.2036   0.08874   0.08264  -0.0334   0.0423   1.0000
  16.000   1.1988   0.09365   0.08766  -0.0356   0.0413   1.0000
  16.250   1.1957   0.09834   0.09252  -0.0378   0.0402   1.0000
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