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-L-100 (fx79l100-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 79-L-100 (fx79l100-il)
Reynolds number: 50,000
Max Cl/Cd: 26.98 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx79l100-il-50000-n5.txt
Download as CSV file: xf-fx79l100-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7189   0.09755   0.09019  -0.0084   1.0000   0.0529
 -11.000  -0.7332   0.09035   0.08300  -0.0129   1.0000   0.0526
 -10.750  -0.7483   0.08392   0.07655  -0.0171   1.0000   0.0523
 -10.500  -0.7696   0.07760   0.07015  -0.0210   1.0000   0.0521
 -10.250  -0.7866   0.07276   0.06523  -0.0231   1.0000   0.0518
 -10.000  -0.8064   0.06838   0.06072  -0.0234   1.0000   0.0518
  -9.750  -0.8215   0.06420   0.05631  -0.0229   1.0000   0.0518
  -9.500  -0.8317   0.06005   0.05184  -0.0221   1.0000   0.0521
  -9.250  -0.8381   0.05605   0.04739  -0.0210   1.0000   0.0527
  -9.000  -0.8319   0.05287   0.04412  -0.0202   1.0000   0.0546
  -8.750  -0.8217   0.05037   0.04148  -0.0194   1.0000   0.0570
  -8.500  -0.8129   0.04734   0.03809  -0.0182   1.0000   0.0592
  -8.250  -0.8019   0.04408   0.03438  -0.0170   1.0000   0.0609
  -8.000  -0.7875   0.04107   0.03086  -0.0158   1.0000   0.0633
  -7.750  -0.7705   0.03853   0.02798  -0.0148   1.0000   0.0668
  -7.500  -0.7508   0.03662   0.02598  -0.0140   1.0000   0.0711
  -7.250  -0.7287   0.03447   0.02351  -0.0131   1.0000   0.0752
  -7.000  -0.7061   0.03259   0.02141  -0.0123   1.0000   0.0806
  -6.750  -0.6839   0.03109   0.01985  -0.0114   1.0000   0.0877
  -6.500  -0.6598   0.02950   0.01811  -0.0105   1.0000   0.0941
  -6.250  -0.6384   0.02822   0.01679  -0.0095   1.0000   0.1039
  -6.000  -0.6181   0.02692   0.01551  -0.0083   1.0000   0.1145
  -5.750  -0.5987   0.02566   0.01423  -0.0070   1.0000   0.1283
  -5.500  -0.5801   0.02441   0.01303  -0.0057   1.0000   0.1479
  -5.250  -0.5631   0.02304   0.01185  -0.0043   1.0000   0.1746
  -5.000  -0.5476   0.02150   0.01073  -0.0029   1.0000   0.2267
  -4.750  -0.5347   0.01994   0.00998  -0.0009   1.0000   0.3335
  -4.500  -0.5203   0.01928   0.00991   0.0019   1.0000   0.4592
  -4.250  -0.5033   0.01912   0.00988   0.0047   1.0000   0.5327
  -4.000  -0.4857   0.01906   0.00983   0.0074   1.0000   0.5838
  -3.750  -0.4680   0.01904   0.00980   0.0101   1.0000   0.6252
  -3.500  -0.4501   0.01904   0.00981   0.0130   1.0000   0.6612
  -3.250  -0.4319   0.01903   0.00980   0.0158   1.0000   0.6930
  -3.000  -0.4137   0.01895   0.00970   0.0184   1.0000   0.7209
  -2.750  -0.3944   0.01883   0.00957   0.0207   1.0000   0.7447
  -2.500  -0.3757   0.01864   0.00931   0.0226   1.0000   0.7654
  -2.250  -0.3557   0.01845   0.00909   0.0242   1.0000   0.7831
  -2.000  -0.3363   0.01826   0.00887   0.0256   1.0000   0.8001
  -1.750  -0.3172   0.01810   0.00867   0.0269   1.0000   0.8170
  -1.500  -0.2977   0.01797   0.00851   0.0279   1.0000   0.8345
  -1.250  -0.2555   0.01793   0.00838   0.0246   0.9853   0.8504
  -1.000  -0.2083   0.01794   0.00832   0.0204   0.9712   0.8659
  -0.750  -0.1590   0.01795   0.00826   0.0158   0.9580   0.8806
  -0.500  -0.1066   0.01797   0.00824   0.0107   0.9462   0.8946
  -0.250  -0.0534   0.01798   0.00822   0.0053   0.9337   0.9078
   0.000   0.0000   0.01798   0.00822   0.0000   0.9210   0.9211
   0.250   0.0533   0.01798   0.00822  -0.0054   0.9078   0.9337
   0.500   0.1063   0.01797   0.00824  -0.0107   0.8946   0.9462
   0.750   0.1589   0.01795   0.00826  -0.0158   0.8807   0.9580
   1.000   0.2080   0.01794   0.00831  -0.0204   0.8659   0.9711
   1.250   0.2553   0.01793   0.00838  -0.0246   0.8505   0.9852
   1.500   0.2976   0.01797   0.00852  -0.0280   0.8345   1.0000
   1.750   0.3171   0.01810   0.00867  -0.0270   0.8172   1.0000
   2.000   0.3362   0.01826   0.00887  -0.0257   0.8003   1.0000
   2.250   0.3556   0.01845   0.00909  -0.0242   0.7832   1.0000
   2.500   0.3756   0.01864   0.00931  -0.0227   0.7655   1.0000
   2.750   0.3944   0.01883   0.00956  -0.0207   0.7449   1.0000
   3.000   0.4136   0.01895   0.00971  -0.0185   0.7213   1.0000
   3.250   0.4318   0.01903   0.00980  -0.0159   0.6932   1.0000
   3.500   0.4500   0.01904   0.00983  -0.0130   0.6611   1.0000
   3.750   0.4679   0.01904   0.00980  -0.0101   0.6253   1.0000
   4.000   0.4856   0.01906   0.00982  -0.0074   0.5837   1.0000
   4.250   0.5033   0.01912   0.00987  -0.0047   0.5333   1.0000
   4.500   0.5201   0.01928   0.00991  -0.0019   0.4583   1.0000
   4.750   0.5348   0.01993   0.00998   0.0009   0.3358   1.0000
   5.000   0.5476   0.02148   0.01073   0.0029   0.2275   1.0000
   5.250   0.5630   0.02303   0.01185   0.0043   0.1745   1.0000
   5.500   0.5800   0.02441   0.01302   0.0057   0.1478   1.0000
   5.750   0.5986   0.02564   0.01421   0.0070   0.1282   1.0000
   6.000   0.6181   0.02691   0.01550   0.0083   0.1148   1.0000
   6.250   0.6384   0.02823   0.01678   0.0094   0.1045   1.0000
   6.500   0.6599   0.02949   0.01812   0.0105   0.0943   1.0000
   6.750   0.6838   0.03108   0.01984   0.0114   0.0878   1.0000
   7.000   0.7058   0.03257   0.02139   0.0123   0.0804   1.0000
   7.250   0.7287   0.03447   0.02352   0.0131   0.0751   1.0000
   7.500   0.7508   0.03663   0.02599   0.0140   0.0711   1.0000
   7.750   0.7704   0.03855   0.02800   0.0148   0.0667   1.0000
   8.000   0.7872   0.04109   0.03090   0.0158   0.0630   1.0000
   8.250   0.8017   0.04412   0.03443   0.0170   0.0608   1.0000
   8.500   0.8127   0.04734   0.03808   0.0182   0.0590   1.0000
   8.750   0.8220   0.05030   0.04139   0.0193   0.0568   1.0000
   9.000   0.8334   0.05261   0.04376   0.0201   0.0540   1.0000
   9.250   0.8377   0.05608   0.04743   0.0210   0.0527   1.0000
   9.500   0.8303   0.06015   0.05196   0.0221   0.0519   1.0000
   9.750   0.8203   0.06432   0.05644   0.0229   0.0517   1.0000
  10.000   0.8049   0.06851   0.06086   0.0233   0.0517   1.0000
  10.250   0.7861   0.07283   0.06530   0.0230   0.0518   1.0000
  10.500   0.7681   0.07782   0.07038   0.0208   0.0521   1.0000
  10.750   0.7458   0.08436   0.07698   0.0165   0.0522   1.0000
  11.000   0.7317   0.09071   0.08335   0.0125   0.0526   1.0000
  11.250   0.7188   0.09771   0.09036   0.0081   0.0529   1.0000
<< Back to FX 79-L-100 (fx79l100-il)

Polar data table (+)

Polar graphs


<< Back to FX 79-L-100 (fx79l100-il)