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Fage & Collins 3 (fg3-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Fage & Collins 3 (fg3-il)
Reynolds number: 100,000
Max Cl/Cd: 49.71 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fg3-il-100000-n5.txt
Download as CSV file: xf-fg3-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Fage & Collins 3                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3680   0.10280   0.09848  -0.0310   1.0000   0.0349
  -8.000  -0.3819   0.10121   0.09697  -0.0289   1.0000   0.0349
  -7.750  -0.3939   0.09925   0.09506  -0.0280   1.0000   0.0350
  -7.500  -0.3898   0.09561   0.09141  -0.0311   0.9974   0.0351
  -7.250  -0.3800   0.09016   0.08601  -0.0313   0.9945   0.0357
  -7.000  -0.3682   0.08630   0.08217  -0.0308   0.9913   0.0366
  -6.750  -0.3532   0.08291   0.07876  -0.0325   0.9873   0.0402
  -6.500  -0.3374   0.07858   0.07436  -0.0379   0.9804   0.0427
  -6.250  -0.2535   0.05886   0.05486  -0.0487   0.9591   0.0483
  -6.000  -0.2415   0.05486   0.05081  -0.0506   0.9539   0.0502
  -5.750  -0.2898   0.06549   0.06097  -0.0495   0.9608   0.0478
  -5.500  -0.2703   0.06204   0.05745  -0.0513   0.9564   0.0506
  -5.250  -0.2453   0.06019   0.05488  -0.0549   0.9465   0.0580
  -5.000  -0.2283   0.05432   0.04931  -0.0561   0.9433   0.0609
  -4.750  -0.2039   0.05267   0.04709  -0.0574   0.9327   0.0722
  -4.500  -0.1810   0.04794   0.04259  -0.0588   0.9250   0.0771
  -4.250  -0.1480   0.04445   0.03868  -0.0614   0.9166   0.0890
  -4.000  -0.1230   0.04150   0.03561  -0.0617   0.9068   0.0947
  -3.750  -0.0844   0.03601   0.02926  -0.0617   0.9019   0.0538
  -3.500  -0.0632   0.03293   0.02542  -0.0590   0.8933   0.0468
  -3.250  -0.0315   0.03048   0.02257  -0.0595   0.8884   0.0470
  -3.000  -0.0079   0.02879   0.02076  -0.0589   0.8807   0.0492
  -2.750   0.0244   0.02686   0.01838  -0.0591   0.8748   0.0489
  -2.500   0.0529   0.02533   0.01647  -0.0585   0.8672   0.0483
  -2.250   0.0863   0.02401   0.01493  -0.0593   0.8602   0.0500
  -2.000   0.1135   0.02302   0.01373  -0.0588   0.8509   0.0521
  -1.750   0.1531   0.02172   0.01219  -0.0605   0.8440   0.0519
  -1.500   0.1775   0.02089   0.01123  -0.0593   0.8324   0.0520
  -1.250   0.2045   0.02008   0.01033  -0.0587   0.8204   0.0523
  -1.000   0.2319   0.01934   0.00951  -0.0582   0.8082   0.0528
  -0.750   0.2578   0.01872   0.00885  -0.0574   0.7936   0.0544
  -0.500   0.2839   0.01819   0.00827  -0.0566   0.7775   0.0568
  -0.250   0.3120   0.01761   0.00760  -0.0562   0.7594   0.0578
   0.000   0.3425   0.01708   0.00696  -0.0563   0.7396   0.0584
   0.250   0.3738   0.01663   0.00636  -0.0565   0.7143   0.0597
   0.500   0.4087   0.01630   0.00581  -0.0576   0.6833   0.0617
   0.750   0.4437   0.01613   0.00538  -0.0587   0.6446   0.0651
   1.000   0.4760   0.01611   0.00506  -0.0593   0.6025   0.0706
   1.500   0.6590   0.01499   0.00528  -0.0879   0.5005   1.0000
   1.750   0.6799   0.01532   0.00538  -0.0865   0.4795   1.0000
   2.000   0.7013   0.01565   0.00550  -0.0853   0.4629   1.0000
   2.250   0.7231   0.01597   0.00566  -0.0841   0.4487   1.0000
   2.500   0.7451   0.01629   0.00584  -0.0831   0.4367   1.0000
   3.000   0.7896   0.01694   0.00627  -0.0810   0.4157   1.0000
   3.250   0.8120   0.01727   0.00650  -0.0801   0.4069   1.0000
   3.500   0.8344   0.01760   0.00676  -0.0792   0.3984   1.0000
   3.750   0.8572   0.01794   0.00707  -0.0783   0.3910   1.0000
   4.000   0.8801   0.01828   0.00737  -0.0775   0.3842   1.0000
   4.250   0.9032   0.01865   0.00770  -0.0768   0.3783   1.0000
   4.500   0.9261   0.01900   0.00808  -0.0760   0.3719   1.0000
   4.750   0.9491   0.01939   0.00843  -0.0753   0.3664   1.0000
   5.000   0.9719   0.01976   0.00885  -0.0745   0.3606   1.0000
   5.250   0.9946   0.02015   0.00926  -0.0737   0.3549   1.0000
   5.500   1.0184   0.02058   0.00970  -0.0732   0.3508   1.0000
   5.750   1.0410   0.02099   0.01022  -0.0724   0.3458   1.0000
   6.000   1.0641   0.02142   0.01073  -0.0717   0.3413   1.0000
   6.250   1.0876   0.02188   0.01123  -0.0712   0.3374   1.0000
   6.500   1.1105   0.02236   0.01183  -0.0705   0.3332   1.0000
   6.750   1.1323   0.02282   0.01245  -0.0696   0.3285   1.0000
   7.000   1.1550   0.02331   0.01305  -0.0689   0.3246   1.0000
   7.500   1.1914   0.02408   0.01409  -0.0658   0.3104   1.0000
   7.750   1.2024   0.02428   0.01438  -0.0628   0.2981   1.0000
   8.000   1.2172   0.02459   0.01476  -0.0605   0.2895   1.0000
   8.250   1.2284   0.02486   0.01519  -0.0577   0.2781   1.0000
   8.500   1.2367   0.02513   0.01559  -0.0543   0.2635   1.0000
   8.750   1.2432   0.02546   0.01603  -0.0506   0.2466   1.0000
   9.000   1.2451   0.02587   0.01647  -0.0462   0.2180   1.0000
   9.250   1.2418   0.02688   0.01716  -0.0415   0.1512   1.0000
   9.500   1.2191   0.02986   0.01932  -0.0351   0.0581   1.0000
   9.750   1.2095   0.03222   0.02157  -0.0305   0.0381   1.0000
  10.000   1.2092   0.03392   0.02341  -0.0273   0.0331   1.0000
  10.250   1.2048   0.03597   0.02559  -0.0240   0.0294   1.0000
  10.500   1.2046   0.03776   0.02758  -0.0214   0.0279   1.0000
  10.750   1.1996   0.04003   0.03004  -0.0189   0.0254   1.0000
  11.000   1.1944   0.04245   0.03265  -0.0167   0.0247   1.0000
  11.250   1.1849   0.04543   0.03583  -0.0149   0.0240   1.0000
  11.500   1.1732   0.04892   0.03952  -0.0136   0.0235   1.0000
  11.750   1.1577   0.05322   0.04400  -0.0131   0.0231   1.0000
  12.000   1.1433   0.05788   0.04887  -0.0135   0.0229   1.0000
  12.250   1.1251   0.06357   0.05475  -0.0147   0.0227   1.0000
  12.500   1.1100   0.06925   0.06061  -0.0163   0.0227   1.0000
  12.750   1.0952   0.07509   0.06657  -0.0181   0.0226   1.0000
  13.000   1.0824   0.08062   0.07227  -0.0197   0.0225   1.0000
  13.250   1.0723   0.08566   0.07743  -0.0210   0.0223   1.0000
  13.500   1.0641   0.09031   0.08224  -0.0220   0.0221   1.0000
  13.750   1.0585   0.09445   0.08649  -0.0228   0.0215   1.0000
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