Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

FX 79-W-151 A (fx79w151a-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 79-W-151 A (fx79w151a-il)
Reynolds number: 100,000
Max Cl/Cd: 46.99 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx79w151a-il-100000-n5.txt
Download as CSV file: xf-fx79w151a-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 79-W-151 A                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.3846   0.09667   0.09189  -0.0573   1.0000   0.0358
 -11.750  -0.4446   0.08035   0.07571  -0.0654   1.0000   0.0361
 -11.500  -0.4966   0.06696   0.06235  -0.0737   1.0000   0.0350
 -11.250  -0.5463   0.05728   0.05263  -0.0804   1.0000   0.0333
 -11.000  -0.5796   0.04955   0.04457  -0.0877   0.9807   0.0331
 -10.750  -0.5901   0.04441   0.03898  -0.0912   0.9626   0.0339
 -10.500  -0.5920   0.04063   0.03473  -0.0920   0.9477   0.0349
 -10.250  -0.5891   0.03762   0.03125  -0.0916   0.9346   0.0367
 -10.000  -0.5723   0.03665   0.03028  -0.0914   0.9240   0.0387
  -9.750  -0.5585   0.03514   0.02855  -0.0907   0.9142   0.0408
  -9.500  -0.5495   0.03330   0.02635  -0.0890   0.9030   0.0433
  -9.250  -0.5384   0.03172   0.02446  -0.0872   0.8927   0.0461
  -9.000  -0.5207   0.03101   0.02370  -0.0862   0.8847   0.0491
  -8.750  -0.5066   0.02995   0.02240  -0.0844   0.8746   0.0525
  -8.500  -0.4900   0.02869   0.02082  -0.0829   0.8665   0.0564
  -8.250  -0.4719   0.02815   0.02026  -0.0817   0.8578   0.0603
  -8.000  -0.4532   0.02725   0.01910  -0.0803   0.8498   0.0651
  -7.750  -0.4340   0.02653   0.01826  -0.0791   0.8420   0.0698
  -7.500  -0.4142   0.02591   0.01752  -0.0779   0.8343   0.0749
  -7.250  -0.3934   0.02513   0.01648  -0.0767   0.8268   0.0808
  -7.000  -0.3728   0.02468   0.01598  -0.0756   0.8194   0.0866
  -6.750  -0.3509   0.02403   0.01509  -0.0746   0.8121   0.0935
  -6.500  -0.3293   0.02359   0.01462  -0.0736   0.8052   0.0999
  -6.250  -0.3070   0.02308   0.01390  -0.0726   0.7976   0.1076
  -6.000  -0.2841   0.02261   0.01338  -0.0717   0.7916   0.1146
  -5.750  -0.2618   0.02220   0.01281  -0.0708   0.7836   0.1227
  -5.500  -0.2378   0.02173   0.01229  -0.0700   0.7781   0.1302
  -5.250  -0.2154   0.02137   0.01182  -0.0691   0.7701   0.1383
  -5.000  -0.1914   0.02097   0.01134  -0.0684   0.7642   0.1468
  -4.750  -0.1684   0.02061   0.01093  -0.0676   0.7572   0.1553
  -4.500  -0.1443   0.02026   0.01049  -0.0669   0.7507   0.1645
  -4.250  -0.1205   0.01988   0.01008  -0.0661   0.7447   0.1730
  -4.000  -0.0973   0.01959   0.00974  -0.0653   0.7375   0.1837
  -3.750  -0.0724   0.01923   0.00932  -0.0646   0.7324   0.1952
  -3.500  -0.0504   0.01897   0.00910  -0.0637   0.7248   0.2075
  -3.250  -0.0262   0.01864   0.00877  -0.0629   0.7190   0.2238
  -3.000  -0.0030   0.01839   0.00852  -0.0621   0.7127   0.2439
  -2.750   0.0199   0.01809   0.00830  -0.0612   0.7061   0.2685
  -2.500   0.0445   0.01771   0.00800  -0.0605   0.7013   0.3061
  -2.250   0.0652   0.01744   0.00793  -0.0594   0.6938   0.3566
  -2.000   0.0882   0.01701   0.00775  -0.0584   0.6883   0.4305
  -1.750   0.1101   0.01664   0.00771  -0.0572   0.6820   0.5212
  -1.500   0.1350   0.01628   0.00770  -0.0564   0.6758   0.6241
  -1.250   0.1724   0.01595   0.00765  -0.0575   0.6712   0.7342
  -1.000   0.2239   0.01599   0.00785  -0.0618   0.6638   0.8201
  -0.750   0.2763   0.01607   0.00785  -0.0661   0.6583   0.8722
  -0.500   0.3229   0.01623   0.00791  -0.0695   0.6520   0.9073
  -0.250   0.3650   0.01643   0.00799  -0.0720   0.6455   0.9359
   0.000   0.4153   0.01654   0.00793  -0.0762   0.6404   0.9576
   0.250   0.4628   0.01671   0.00803  -0.0804   0.6328   0.9780
   0.500   0.5190   0.01667   0.00783  -0.0863   0.6272   0.9936
   0.750   0.5542   0.01674   0.00784  -0.0883   0.6207   1.0000
   1.000   0.5743   0.01680   0.00782  -0.0872   0.6146   1.0000
   1.250   0.5956   0.01684   0.00776  -0.0862   0.6096   1.0000
   1.500   0.6144   0.01702   0.00793  -0.0849   0.6027   1.0000
   1.750   0.6359   0.01710   0.00793  -0.0839   0.5975   1.0000
   2.000   0.6561   0.01726   0.00805  -0.0827   0.5917   1.0000
   2.250   0.6762   0.01744   0.00821  -0.0815   0.5855   1.0000
   2.500   0.6989   0.01753   0.00821  -0.0806   0.5808   1.0000
   2.750   0.7178   0.01779   0.00849  -0.0793   0.5744   1.0000
   3.000   0.7390   0.01796   0.00863  -0.0782   0.5688   1.0000
   3.250   0.7619   0.01810   0.00872  -0.0774   0.5643   1.0000
   3.500   0.7801   0.01842   0.00909  -0.0759   0.5579   1.0000
   3.750   0.8020   0.01861   0.00925  -0.0749   0.5528   1.0000
   4.000   0.8237   0.01883   0.00944  -0.0739   0.5478   1.0000
   4.250   0.8423   0.01915   0.00983  -0.0725   0.5415   1.0000
   4.500   0.8648   0.01935   0.01001  -0.0716   0.5369   1.0000
   4.750   0.8854   0.01964   0.01032  -0.0705   0.5319   1.0000
   5.000   0.9039   0.02000   0.01075  -0.0691   0.5261   1.0000
   5.250   0.9269   0.02020   0.01094  -0.0682   0.5214   1.0000
   5.500   0.9460   0.02056   0.01136  -0.0669   0.5161   1.0000
   5.750   0.9644   0.02095   0.01182  -0.0655   0.5107   1.0000
   6.000   0.9875   0.02118   0.01208  -0.0647   0.5064   1.0000
   6.250   1.0061   0.02158   0.01255  -0.0633   0.5012   1.0000
   6.500   1.0234   0.02202   0.01308  -0.0618   0.4957   1.0000
   6.750   1.0465   0.02227   0.01336  -0.0610   0.4914   1.0000
   7.000   1.0654   0.02271   0.01390  -0.0597   0.4869   1.0000
   7.250   1.0804   0.02325   0.01456  -0.0579   0.4813   1.0000
   7.500   1.1028   0.02354   0.01491  -0.0570   0.4769   1.0000
   7.750   1.1222   0.02396   0.01541  -0.0558   0.4723   1.0000
   8.000   1.1343   0.02460   0.01619  -0.0536   0.4665   1.0000
   8.250   1.1557   0.02495   0.01664  -0.0527   0.4622   1.0000
   8.500   1.1765   0.02534   0.01712  -0.0516   0.4578   1.0000
   8.750   1.1840   0.02612   0.01808  -0.0488   0.4519   1.0000
   9.000   1.2057   0.02640   0.01843  -0.0479   0.4467   1.0000
   9.250   1.2185   0.02697   0.01913  -0.0458   0.4410   1.0000
   9.500   1.2275   0.02757   0.01989  -0.0431   0.4342   1.0000
   9.750   1.2486   0.02775   0.02014  -0.0420   0.4279   1.0000
  10.000   1.2447   0.02860   0.02114  -0.0376   0.4201   1.0000
  10.250   1.2531   0.02892   0.02151  -0.0347   0.4108   1.0000
  10.500   1.2544   0.02929   0.02191  -0.0310   0.3975   1.0000
  10.750   1.2485   0.03018   0.02282  -0.0271   0.3823   1.0000
  11.000   1.2382   0.03162   0.02430  -0.0234   0.3649   1.0000
  11.250   1.2307   0.03330   0.02601  -0.0206   0.3475   1.0000
  11.500   1.2226   0.03522   0.02791  -0.0181   0.3265   1.0000
  11.750   1.2142   0.03764   0.03039  -0.0161   0.3078   1.0000
  12.000   1.2061   0.04028   0.03304  -0.0145   0.2867   1.0000
  12.250   1.1987   0.04302   0.03576  -0.0132   0.2632   1.0000
  12.500   1.1894   0.04603   0.03868  -0.0120   0.2361   1.0000
  12.750   1.1732   0.04988   0.04232  -0.0109   0.2023   1.0000
  13.000   1.1550   0.05425   0.04648  -0.0102   0.1732   1.0000
  13.250   1.1408   0.05848   0.05061  -0.0099   0.1522   1.0000
  13.500   1.1234   0.06328   0.05528  -0.0098   0.1282   1.0000
  13.750   1.1066   0.06821   0.06009  -0.0100   0.1050   1.0000
  14.000   1.0912   0.07314   0.06491  -0.0103   0.0853   1.0000
  14.250   1.0805   0.07759   0.06932  -0.0107   0.0715   1.0000
  14.500   1.0690   0.08227   0.07392  -0.0113   0.0584   1.0000
  14.750   1.0598   0.08674   0.07838  -0.0118   0.0497   1.0000
  15.000   1.0510   0.09124   0.08284  -0.0125   0.0434   1.0000
  15.250   1.0473   0.09509   0.08678  -0.0130   0.0394   1.0000
<< Back to FX 79-W-151 A (fx79w151a-il)

Polar data table (+)

Polar graphs


<< Back to FX 79-W-151 A (fx79w151a-il)