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FX 79-W-151 A (fx79w151a-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 79-W-151 A (fx79w151a-il)
Reynolds number: 50,000
Max Cl/Cd: 4.85 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx79w151a-il-50000.txt
Download as CSV file: xf-fx79w151a-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2997   0.12051   0.11421  -0.0401   1.0000   0.2596
 -10.250  -0.2742   0.11521   0.10888  -0.0382   1.0000   0.2709
 -10.000  -0.3101   0.11650   0.11040  -0.0364   1.0000   0.2751
  -9.750  -0.2944   0.11274   0.10664  -0.0334   1.0000   0.2880
  -9.500  -0.3308   0.11386   0.10795  -0.0300   1.0000   0.2906
  -9.250  -0.3236   0.11113   0.10525  -0.0266   1.0000   0.3041
  -9.000  -0.3619   0.11220   0.10651  -0.0232   1.0000   0.3064
  -8.750  -0.3506   0.10911   0.10343  -0.0203   1.0000   0.3196
  -8.500  -0.3676   0.10791   0.10233  -0.0174   1.0000   0.3254
  -8.250  -0.3796   0.10693   0.10142  -0.0144   1.0000   0.3358
  -8.000  -0.3854   0.10485   0.09941  -0.0118   1.0000   0.3435
  -7.750  -0.4168   0.10502   0.09972  -0.0085   1.0000   0.3529
  -7.500  -0.4136   0.10262   0.09734  -0.0058   1.0000   0.3667
  -7.250  -0.4189   0.10083   0.09560  -0.0030   1.0000   0.3809
  -7.000  -0.4265   0.09908   0.09390  -0.0001   1.0000   0.3945
  -6.750  -0.4361   0.09745   0.09234   0.0030   1.0000   0.4096
  -6.500  -0.6372   0.07651   0.07112  -0.0201   1.0000   0.1818
  -6.250  -0.6216   0.07100   0.06541  -0.0227   0.9939   0.1805
  -6.000  -0.6093   0.06555   0.05965  -0.0251   0.9877   0.1786
  -5.750  -0.5979   0.06027   0.05393  -0.0268   0.9813   0.1772
  -5.500  -0.5886   0.05587   0.04886  -0.0274   0.9751   0.1806
  -5.250  -0.5664   0.05305   0.04582  -0.0284   0.9685   0.1871
  -5.000  -0.5485   0.05031   0.04256  -0.0284   0.9615   0.1938
  -4.750  -0.5263   0.04832   0.04027  -0.0288   0.9543   0.2037
  -4.500  -0.5064   0.04626   0.03744  -0.0287   0.9477   0.2127
  -4.250  -0.4823   0.04513   0.03622  -0.0289   0.9405   0.2260
  -4.000  -0.4571   0.04388   0.03477  -0.0293   0.9332   0.2370
  -3.750  -0.4338   0.04306   0.03372  -0.0293   0.9262   0.2521
  -3.500  -0.4099   0.04224   0.03266  -0.0293   0.9192   0.2656
  -3.250  -0.3839   0.04173   0.03197  -0.0297   0.9116   0.2820
  -3.000  -0.3603   0.04122   0.03130  -0.0297   0.9046   0.2971
  -2.750  -0.3319   0.04094   0.03090  -0.0304   0.8973   0.3163
  -2.500  -0.3084   0.04068   0.03052  -0.0304   0.8898   0.3361
  -2.250  -0.2763   0.04053   0.03040  -0.0317   0.8823   0.3620
  -2.000  -0.2497   0.04038   0.03030  -0.0323   0.8749   0.3922
  -1.750   0.0023   0.03955   0.03180  -0.0690   0.8587   1.0000
  -1.500   0.0082   0.03995   0.03182  -0.0673   0.8513   1.0000
  -1.250   0.0128   0.04050   0.03205  -0.0649   0.8440   1.0000
  -1.000   0.0313   0.04125   0.03248  -0.0646   0.8366   1.0000
  -0.750   0.0355   0.04195   0.03295  -0.0620   0.8296   1.0000
  -0.500   0.0613   0.04285   0.03357  -0.0626   0.8222   1.0000
  -0.250   0.0612   0.04365   0.03419  -0.0594   0.8157   1.0000
   0.000   0.0936   0.04468   0.03496  -0.0609   0.8088   1.0000
   0.250   0.0890   0.04558   0.03572  -0.0573   0.8030   1.0000
   0.500   0.1037   0.04658   0.03655  -0.0563   0.7971   1.0000
   0.750   0.1236   0.04773   0.03750  -0.0561   0.7910   1.0000
   1.000   0.1249   0.04880   0.03846  -0.0536   0.7866   1.0000
   1.250   0.1394   0.04998   0.03950  -0.0528   0.7820   1.0000
   1.500   0.1608   0.05127   0.04064  -0.0529   0.7760   1.0000
   1.750   0.1634   0.05258   0.04186  -0.0508   0.7744   1.0000
   2.000   0.1694   0.05399   0.04317  -0.0494   0.7739   1.0000
   2.250   0.1806   0.05568   0.04476  -0.0488   0.7761   1.0000
   2.500   0.0735   0.05754   0.04679  -0.0367   0.8992   1.0000
   2.750   0.0926   0.05875   0.04789  -0.0370   0.8873   1.0000
   3.000   0.1060   0.05995   0.04900  -0.0364   0.8793   1.0000
   3.250   0.1379   0.06252   0.05146  -0.0389   0.8703   1.0000
   3.500   0.1468   0.06318   0.05205  -0.0375   0.8594   1.0000
   3.750   0.1722   0.06556   0.05434  -0.0390   0.8534   1.0000
   4.000   0.1861   0.06661   0.05533  -0.0385   0.8424   1.0000
   4.250   0.2005   0.06813   0.05680  -0.0382   0.8345   1.0000
   4.500   0.2276   0.07039   0.05901  -0.0397   0.8252   1.0000
   4.750   0.2345   0.07131   0.05989  -0.0383   0.8162   1.0000
   5.000   0.2652   0.07416   0.06269  -0.0405   0.8091   1.0000
   5.250   0.2686   0.07476   0.06328  -0.0386   0.7994   1.0000
   5.500   0.3020   0.07808   0.06657  -0.0411   0.7929   1.0000
   5.750   0.3038   0.07841   0.06689  -0.0391   0.7821   1.0000
   6.000   0.3257   0.08097   0.06943  -0.0401   0.7764   1.0000
   6.250   0.3385   0.08227   0.07074  -0.0396   0.7654   1.0000
   6.500   0.3499   0.08401   0.07249  -0.0392   0.7585   1.0000
   6.750   0.3707   0.08614   0.07463  -0.0399   0.7495   1.0000
   7.000   0.3780   0.08763   0.07613  -0.0390   0.7416   1.0000
   7.250   0.4044   0.09036   0.07889  -0.0404   0.7333   1.0000
   7.500   0.4071   0.09145   0.08001  -0.0390   0.7239   1.0000
   7.750   0.4386   0.09496   0.08358  -0.0411   0.7172   1.0000
   8.000   0.4368   0.09555   0.08419  -0.0392   0.7067   1.0000
   8.250   0.4621   0.09888   0.08757  -0.0407   0.7007   1.0000
   8.500   0.4676   0.09997   0.08871  -0.0397   0.6896   1.0000
   8.750   0.4771   0.10204   0.09085  -0.0394   0.6820   1.0000
   9.000   0.4998   0.10481   0.09369  -0.0404   0.6727   1.0000
   9.250   0.5013   0.10619   0.09512  -0.0393   0.6629   1.0000
   9.500   0.5362   0.11060   0.09962  -0.0417   0.6559   1.0000
   9.750   0.5307   0.11101   0.10010  -0.0399   0.6443   1.0000
  10.000   0.5385   0.11325   0.10242  -0.0397   0.6357   1.0000
  10.250   0.5653   0.11675   0.10604  -0.0411   0.6265   1.0000
  10.500   0.5629   0.11796   0.10730  -0.0400   0.6155   1.0000
  10.750   0.5766   0.12092   0.11036  -0.0404   0.6077   1.0000
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