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GIII BL145 AIRFOIL (giiif-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GIII BL145 AIRFOIL (giiif-il)
Reynolds number: 100,000
Max Cl/Cd: 46.62 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-giiif-il-100000.txt
Download as CSV file: xf-giiif-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GIII BL145 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4506   0.11589   0.11119  -0.0058   1.0000   0.0756
 -10.250  -0.4548   0.11247   0.10780  -0.0077   1.0000   0.0779
 -10.000  -0.5758   0.11768   0.11278   0.0032   1.0000   0.0698
  -9.750  -0.5702   0.11389   0.10900   0.0027   1.0000   0.0722
  -9.500  -0.5678   0.11009   0.10523   0.0010   1.0000   0.0747
  -9.250  -0.5685   0.10626   0.10145  -0.0020   1.0000   0.0773
  -9.000  -0.5761   0.10250   0.09777  -0.0081   1.0000   0.0792
  -8.750  -0.5880   0.09828   0.09361  -0.0161   1.0000   0.0797
  -8.500  -0.6007   0.09500   0.09026  -0.0215   1.0000   0.0801
  -8.250  -0.5781   0.08844   0.08384  -0.0158   1.0000   0.0828
  -8.000  -0.5722   0.08476   0.08017  -0.0157   1.0000   0.0857
  -7.750  -0.5715   0.08065   0.07605  -0.0184   1.0000   0.0889
  -7.500  -0.5791   0.07721   0.07240  -0.0246   1.0000   0.0932
  -7.000  -0.5635   0.06790   0.06312  -0.0243   1.0000   0.0985
  -6.750  -0.5557   0.06444   0.05954  -0.0251   1.0000   0.1046
  -6.500  -0.5007   0.04792   0.04337  -0.0266   1.0000   0.1142
  -6.250  -0.5042   0.04405   0.03919  -0.0267   1.0000   0.1228
  -6.000  -0.4935   0.04057   0.03582  -0.0251   1.0000   0.1317
  -5.750  -0.4892   0.03709   0.03229  -0.0235   1.0000   0.1424
  -5.500  -0.4853   0.03396   0.02908  -0.0217   1.0000   0.1551
  -5.250  -0.4984   0.04480   0.03921  -0.0212   1.0000   0.1688
  -5.000  -0.4876   0.04229   0.03660  -0.0194   1.0000   0.1866
  -4.750  -0.4535   0.03441   0.02707  -0.0174   1.0000   0.0824
  -4.500  -0.4487   0.03502   0.02826  -0.0166   1.0000   0.1397
  -4.250  -0.4139   0.02788   0.01944  -0.0127   1.0000   0.0652
  -4.000  -0.3951   0.02556   0.01674  -0.0110   1.0000   0.0686
  -3.750  -0.3748   0.02382   0.01490  -0.0098   1.0000   0.0726
  -3.500  -0.3519   0.02203   0.01276  -0.0084   1.0000   0.0753
  -3.250  -0.3283   0.02053   0.01095  -0.0071   1.0000   0.0811
  -3.000  -0.3064   0.01943   0.00979  -0.0061   1.0000   0.0945
  -2.750  -0.2834   0.01797   0.00845  -0.0053   1.0000   0.1105
  -2.500  -0.2619   0.01695   0.00755  -0.0044   1.0000   0.1374
  -2.250  -0.2405   0.01598   0.00681  -0.0036   1.0000   0.1750
  -2.000  -0.2183   0.01454   0.00598  -0.0032   1.0000   0.2753
  -1.750  -0.0326   0.01325   0.00629  -0.0246   1.0000   1.0000
  -1.500  -0.0405   0.01330   0.00630  -0.0196   1.0000   1.0000
  -1.250  -0.0529   0.01335   0.00632  -0.0139   1.0000   1.0000
  -1.000  -0.0629   0.01338   0.00630  -0.0086   1.0000   1.0000
  -0.750  -0.0657   0.01343   0.00626  -0.0044   1.0000   1.0000
  -0.500  -0.0595   0.01354   0.00626  -0.0018   1.0000   1.0000
  -0.250  -0.0445   0.01373   0.00633  -0.0007   0.9995   1.0000
   0.000  -0.0019   0.01406   0.00654  -0.0047   0.9926   1.0000
   0.250   0.0398   0.01439   0.00676  -0.0084   0.9851   1.0000
   0.500   0.0799   0.01471   0.00702  -0.0119   0.9774   1.0000
   0.750   0.1287   0.01504   0.00731  -0.0168   0.9693   1.0000
   1.000   0.1756   0.01525   0.00752  -0.0211   0.9576   1.0000
   1.250   0.2216   0.01542   0.00772  -0.0252   0.9463   1.0000
   1.500   0.2677   0.01559   0.00795  -0.0292   0.9367   1.0000
   1.750   0.3200   0.01567   0.00814  -0.0343   0.9283   1.0000
   2.000   0.3585   0.01578   0.00835  -0.0366   0.9168   1.0000
   2.250   0.3967   0.01586   0.00855  -0.0387   0.9052   1.0000
   2.500   0.4339   0.01589   0.00875  -0.0403   0.8931   1.0000
   2.750   0.4681   0.01590   0.00891  -0.0412   0.8801   1.0000
   3.000   0.4987   0.01589   0.00905  -0.0411   0.8658   1.0000
   3.250   0.5267   0.01585   0.00917  -0.0403   0.8501   1.0000
   3.500   0.5532   0.01538   0.00889  -0.0379   0.8266   1.0000
   3.750   0.5731   0.01462   0.00817  -0.0333   0.7909   1.0000
   4.000   0.5909   0.01408   0.00767  -0.0290   0.7513   1.0000
   4.250   0.6096   0.01370   0.00733  -0.0254   0.7070   1.0000
   4.500   0.6271   0.01345   0.00704  -0.0217   0.6386   1.0000
   4.750   0.6345   0.01416   0.00668  -0.0162   0.4082   1.0000
   5.000   0.6320   0.01773   0.00820  -0.0117   0.1238   1.0000
   5.250   0.6478   0.01941   0.00968  -0.0095   0.0951   1.0000
   5.500   0.6666   0.02098   0.01118  -0.0078   0.0816   1.0000
   5.750   0.6880   0.02268   0.01280  -0.0066   0.0714   1.0000
   6.000   0.7129   0.02450   0.01464  -0.0057   0.0660   1.0000
   6.250   0.7394   0.02753   0.01765  -0.0052   0.0624   1.0000
   6.500   0.7632   0.02901   0.01958  -0.0039   0.0577   1.0000
   6.750   0.7869   0.03164   0.02266  -0.0026   0.0564   1.0000
   7.000   0.8084   0.03492   0.02643  -0.0011   0.0573   1.0000
   7.250   0.8270   0.03881   0.03080   0.0005   0.0597   1.0000
   7.500   0.8431   0.04351   0.03580   0.0018   0.0618   1.0000
   7.750   0.8602   0.04771   0.04029   0.0030   0.0632   1.0000
  10.250   0.7637   0.10963   0.10493  -0.0132   0.1269   1.0000
  10.500   0.7489   0.11516   0.11038  -0.0185   0.1217   1.0000
  10.750   0.6113   0.11249   0.10788  -0.0066   0.1400   1.0000
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