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FX 79-L-100 (fx79l100-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 79-L-100 (fx79l100-il)
Reynolds number: 200,000
Max Cl/Cd: 50.07 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx79l100-il-200000.txt
Download as CSV file: xf-fx79l100-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 79-L-100                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.5525   0.10712   0.10373  -0.0035   1.0000   0.0661
 -11.500  -0.5376   0.10494   0.10152  -0.0016   1.0000   0.0675
 -11.000  -0.6311   0.07157   0.06817  -0.0184   1.0000   0.0439
 -10.750  -0.6095   0.07325   0.06988  -0.0155   1.0000   0.0460
 -10.500  -0.6069   0.07188   0.06854  -0.0164   1.0000   0.0564
 -10.250  -0.8185   0.06431   0.06029  -0.0256   1.0000   0.0409
 -10.000  -0.8340   0.05981   0.05571  -0.0250   1.0000   0.0396
  -9.750  -0.8514   0.05503   0.05071  -0.0238   1.0000   0.0387
  -9.500  -0.8673   0.04925   0.04458  -0.0222   1.0000   0.0369
  -9.250  -0.8919   0.04090   0.03530  -0.0188   1.0000   0.0344
  -9.000  -0.8861   0.03704   0.03100  -0.0168   1.0000   0.0343
  -8.750  -0.8724   0.03467   0.02842  -0.0155   1.0000   0.0353
  -8.500  -0.8552   0.03315   0.02678  -0.0145   1.0000   0.0372
  -8.250  -0.8396   0.03082   0.02411  -0.0129   1.0000   0.0387
  -8.000  -0.8217   0.02898   0.02190  -0.0115   1.0000   0.0405
  -7.750  -0.8020   0.02739   0.01997  -0.0101   1.0000   0.0417
  -7.500  -0.7830   0.02436   0.01677  -0.0091   1.0000   0.0440
  -7.250  -0.7615   0.02337   0.01576  -0.0082   1.0000   0.0474
  -7.000  -0.7390   0.02214   0.01438  -0.0073   1.0000   0.0501
  -6.750  -0.7158   0.02118   0.01321  -0.0062   1.0000   0.0526
  -6.500  -0.6950   0.01941   0.01147  -0.0052   1.0000   0.0569
  -6.250  -0.6727   0.01855   0.01059  -0.0042   1.0000   0.0612
  -6.000  -0.6498   0.01784   0.00975  -0.0031   1.0000   0.0653
  -5.750  -0.6307   0.01657   0.00861  -0.0017   1.0000   0.0720
  -5.500  -0.6088   0.01592   0.00786  -0.0006   1.0000   0.0790
  -5.250  -0.5898   0.01497   0.00701   0.0009   1.0000   0.0879
  -5.000  -0.5699   0.01420   0.00631   0.0023   1.0000   0.1007
  -4.750  -0.5502   0.01346   0.00564   0.0038   1.0000   0.1191
  -4.500  -0.5328   0.01249   0.00497   0.0054   1.0000   0.1601
  -4.250  -0.5208   0.01110   0.00432   0.0078   1.0000   0.2880
  -4.000  -0.5092   0.01017   0.00413   0.0105   1.0000   0.4396
  -3.750  -0.4921   0.00992   0.00413   0.0127   1.0000   0.5128
  -3.500  -0.4744   0.00985   0.00413   0.0147   1.0000   0.5523
  -3.250  -0.4593   0.00986   0.00416   0.0170   1.0000   0.5811
  -3.000  -0.4201   0.00986   0.00418   0.0145   0.9899   0.6120
  -2.750  -0.3766   0.00982   0.00418   0.0113   0.9773   0.6380
  -2.500  -0.3337   0.00979   0.00414   0.0083   0.9647   0.6609
  -2.250  -0.2905   0.00976   0.00414   0.0054   0.9520   0.6833
  -2.000  -0.2486   0.00973   0.00413   0.0028   0.9376   0.7054
  -1.750  -0.2081   0.00969   0.00410   0.0006   0.9220   0.7236
  -1.500  -0.1706   0.00965   0.00405  -0.0011   0.9051   0.7392
  -1.250  -0.1370   0.00962   0.00398  -0.0019   0.8877   0.7522
  -1.000  -0.1072   0.00962   0.00392  -0.0020   0.8708   0.7647
  -0.750  -0.0793   0.00961   0.00389  -0.0017   0.8546   0.7761
  -0.500  -0.0523   0.00960   0.00386  -0.0012   0.8396   0.7872
  -0.250  -0.0259   0.00960   0.00384  -0.0007   0.8255   0.7991
   0.000   0.0000   0.00960   0.00383   0.0000   0.8119   0.8120
   0.250   0.0258   0.00960   0.00384   0.0007   0.7992   0.8256
   0.500   0.0522   0.00960   0.00386   0.0012   0.7872   0.8395
   0.750   0.0793   0.00961   0.00389   0.0017   0.7759   0.8544
   1.000   0.1071   0.00962   0.00392   0.0020   0.7649   0.8707
   1.250   0.1370   0.00962   0.00399   0.0019   0.7523   0.8877
   1.500   0.1705   0.00965   0.00405   0.0011   0.7392   0.9051
   1.750   0.2081   0.00969   0.00410  -0.0006   0.7238   0.9221
   2.000   0.2485   0.00973   0.00412  -0.0028   0.7052   0.9376
   2.250   0.2903   0.00975   0.00414  -0.0054   0.6833   0.9519
   2.500   0.3336   0.00979   0.00415  -0.0084   0.6614   0.9646
   2.750   0.3764   0.00982   0.00417  -0.0113   0.6369   0.9773
   3.000   0.4202   0.00986   0.00418  -0.0145   0.6122   0.9900
   3.250   0.4594   0.00986   0.00418  -0.0171   0.5817   1.0000
   3.500   0.4744   0.00985   0.00413  -0.0147   0.5524   1.0000
   3.750   0.4919   0.00992   0.00412  -0.0127   0.5109   1.0000
   4.000   0.5092   0.01017   0.00413  -0.0106   0.4400   1.0000
   4.250   0.5209   0.01109   0.00432  -0.0078   0.2893   1.0000
   4.500   0.5327   0.01250   0.00496  -0.0055   0.1590   1.0000
   4.750   0.5501   0.01345   0.00563  -0.0038   0.1199   1.0000
   5.000   0.5699   0.01420   0.00630  -0.0023   0.1008   1.0000
   5.250   0.5897   0.01497   0.00702  -0.0009   0.0882   1.0000
   5.500   0.6089   0.01590   0.00785   0.0005   0.0791   1.0000
   5.750   0.6307   0.01658   0.00862   0.0017   0.0725   1.0000
   6.000   0.6503   0.01771   0.00964   0.0030   0.0658   1.0000
   6.250   0.6727   0.01857   0.01060   0.0042   0.0617   1.0000
   6.500   0.6950   0.01940   0.01147   0.0052   0.0571   1.0000
   6.750   0.7158   0.02124   0.01326   0.0062   0.0528   1.0000
   7.000   0.7389   0.02207   0.01431   0.0072   0.0497   1.0000
   7.250   0.7612   0.02302   0.01537   0.0082   0.0464   1.0000
   7.500   0.7826   0.02429   0.01663   0.0090   0.0433   1.0000
   7.750   0.8020   0.02708   0.01969   0.0101   0.0413   1.0000
   8.000   0.8215   0.02886   0.02181   0.0115   0.0400   1.0000
   8.250   0.8393   0.03085   0.02417   0.0130   0.0382   1.0000
   8.500   0.8549   0.03318   0.02682   0.0145   0.0369   1.0000
   8.750   0.8729   0.03456   0.02827   0.0154   0.0351   1.0000
   9.000   0.8850   0.03735   0.03135   0.0169   0.0344   1.0000
   9.250   0.8939   0.04046   0.03476   0.0185   0.0340   1.0000
   9.500   0.8681   0.04906   0.04436   0.0222   0.0365   1.0000
   9.750   0.8501   0.05522   0.05091   0.0238   0.0387   1.0000
  10.000   0.8350   0.05990   0.05578   0.0249   0.0399   1.0000
  10.250   0.8180   0.06437   0.06035   0.0255   0.0408   1.0000
  10.750   0.6163   0.07108   0.06770   0.0169   0.0455   1.0000
  11.000   0.6423   0.06910   0.06566   0.0205   0.0437   1.0000
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