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Fage & Collins 4 (fg4-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: Fage & Collins 4 (fg4-il)
Reynolds number: 200,000
Max Cl/Cd: 46.96 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fg4-il-200000-n5.txt
Download as CSV file: xf-fg4-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Fage & Collins 4                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2159   0.09074   0.08706  -0.0619   0.9670   0.0376
  -8.750  -0.2171   0.08692   0.08325  -0.0657   0.9585   0.0377
  -8.250  -0.1995   0.08073   0.07711  -0.0665   0.9464   0.0381
  -8.000  -0.1866   0.07776   0.07415  -0.0677   0.9420   0.0384
  -7.750  -0.1829   0.07496   0.07135  -0.0684   0.9338   0.0388
  -7.500  -0.1678   0.07141   0.06778  -0.0715   0.9295   0.0396
  -7.250  -0.1584   0.06795   0.06429  -0.0736   0.9216   0.0407
  -7.000  -0.1412   0.06335   0.05959  -0.0786   0.9169   0.0422
  -6.750  -0.1334   0.05725   0.05303  -0.0839   0.9072   0.0434
  -6.500  -0.1125   0.05341   0.04914  -0.0858   0.9033   0.0437
  -6.250  -0.0857   0.05031   0.04605  -0.0880   0.9007   0.0441
  -6.000  -0.0719   0.04816   0.04386  -0.0873   0.8920   0.0447
  -5.750  -0.0452   0.04538   0.04098  -0.0894   0.8872   0.0456
  -5.500  -0.0246   0.04284   0.03830  -0.0898   0.8793   0.0468
  -5.000   0.0091   0.03736   0.03214  -0.0878   0.8594   0.0506
  -4.750   0.0365   0.03511   0.02985  -0.0890   0.8517   0.0513
  -4.500   0.0467   0.03373   0.02841  -0.0860   0.8377   0.0520
  -4.000   0.0707   0.03101   0.02513  -0.0795   0.8062   0.0585
  -3.500   0.1130   0.02491   0.01819  -0.0751   0.7750   0.0372
  -3.250   0.1445   0.02337   0.01642  -0.0759   0.7561   0.0366
  -3.000   0.1778   0.02191   0.01461  -0.0767   0.7345   0.0361
  -2.750   0.2090   0.02075   0.01310  -0.0771   0.7141   0.0357
  -2.500   0.2365   0.01978   0.01181  -0.0766   0.6959   0.0356
  -2.250   0.2618   0.01900   0.01077  -0.0758   0.6804   0.0355
  -2.000   0.2865   0.01839   0.00992  -0.0748   0.6640   0.0359
  -1.750   0.3093   0.01797   0.00924  -0.0733   0.6460   0.0368
  -1.500   0.3318   0.01755   0.00861  -0.0719   0.6303   0.0372
  -1.250   0.3518   0.01714   0.00801  -0.0699   0.6110   0.0373
  -1.000   0.3718   0.01678   0.00751  -0.0680   0.5935   0.0374
  -0.500   0.4113   0.01620   0.00670  -0.0641   0.5627   0.0376
  -0.250   0.4316   0.01588   0.00633  -0.0623   0.5497   0.0379
   0.000   0.4500   0.01561   0.00603  -0.0602   0.5351   0.0384
   0.250   0.4678   0.01545   0.00581  -0.0579   0.5213   0.0388
   0.500   0.4866   0.01528   0.00563  -0.0559   0.5091   0.0394
   0.750   0.5040   0.01518   0.00549  -0.0536   0.4952   0.0401
   1.000   0.5199   0.01514   0.00540  -0.0510   0.4787   0.0415
   1.250   0.5360   0.01516   0.00534  -0.0484   0.4620   0.0432
   1.500   0.5512   0.01515   0.00527  -0.0457   0.4428   0.0441
   1.750   0.5652   0.01521   0.00523  -0.0428   0.4184   0.0451
   2.000   0.5808   0.01532   0.00523  -0.0403   0.3978   0.0464
   2.250   0.5945   0.01552   0.00527  -0.0374   0.3720   0.0474
   2.500   0.6094   0.01573   0.00534  -0.0347   0.3495   0.0493
   2.750   0.6246   0.01596   0.00545  -0.0322   0.3287   0.0515
   3.000   0.6406   0.01621   0.00559  -0.0299   0.3098   0.0566
   3.250   0.6556   0.01648   0.00578  -0.0275   0.2877   0.0711
   3.750   0.8862   0.01887   0.00867  -0.0702   0.0690   1.0000
   4.000   0.8999   0.01937   0.00908  -0.0677   0.0649   1.0000
   4.250   0.9157   0.01976   0.00943  -0.0655   0.0632   1.0000
   4.500   0.9315   0.02015   0.00981  -0.0633   0.0619   1.0000
   4.750   0.9474   0.02055   0.01020  -0.0613   0.0610   1.0000
   5.000   0.9633   0.02095   0.01061  -0.0592   0.0603   1.0000
   5.250   0.9785   0.02140   0.01108  -0.0571   0.0596   1.0000
   5.500   0.9936   0.02186   0.01155  -0.0550   0.0591   1.0000
   5.750   1.0080   0.02237   0.01208  -0.0528   0.0585   1.0000
   6.000   1.0218   0.02292   0.01265  -0.0506   0.0580   1.0000
   6.250   1.0355   0.02349   0.01325  -0.0485   0.0577   1.0000
   6.500   1.0481   0.02412   0.01391  -0.0462   0.0572   1.0000
   6.750   1.0599   0.02481   0.01465  -0.0439   0.0569   1.0000
   7.000   1.0712   0.02553   0.01541  -0.0417   0.0566   1.0000
   7.250   1.0819   0.02631   0.01624  -0.0394   0.0563   1.0000
   7.500   1.0929   0.02710   0.01707  -0.0373   0.0562   1.0000
   7.750   1.1038   0.02790   0.01791  -0.0352   0.0561   1.0000
   8.000   1.1134   0.02881   0.01888  -0.0331   0.0560   1.0000
   8.250   1.1223   0.02979   0.01993  -0.0311   0.0558   1.0000
   8.500   1.1312   0.03081   0.02100  -0.0291   0.0555   1.0000
   8.750   1.1388   0.03195   0.02220  -0.0271   0.0553   1.0000
   9.000   1.1458   0.03318   0.02348  -0.0252   0.0552   1.0000
   9.250   1.1518   0.03451   0.02488  -0.0234   0.0550   1.0000
   9.500   1.1576   0.03593   0.02636  -0.0217   0.0549   1.0000
   9.750   1.1630   0.03744   0.02793  -0.0201   0.0547   1.0000
  10.000   1.1679   0.03905   0.02961  -0.0187   0.0545   1.0000
  10.250   1.1723   0.04078   0.03140  -0.0173   0.0542   1.0000
  10.500   1.1770   0.04254   0.03322  -0.0162   0.0543   1.0000
  10.750   1.1813   0.04443   0.03516  -0.0152   0.0541   1.0000
  11.000   1.1858   0.04633   0.03713  -0.0143   0.0540   1.0000
  11.250   1.1905   0.04825   0.03911  -0.0135   0.0540   1.0000
  11.500   1.1946   0.05029   0.04119  -0.0127   0.0539   1.0000
  11.750   1.2000   0.05223   0.04319  -0.0121   0.0537   1.0000
  12.000   1.2049   0.05423   0.04524  -0.0116   0.0535   1.0000
  12.250   1.2096   0.05628   0.04735  -0.0110   0.0532   1.0000
  12.500   1.2145   0.05835   0.04946  -0.0106   0.0528   1.0000
  12.750   1.2192   0.06043   0.05157  -0.0102   0.0522   1.0000
  13.000   1.2246   0.06239   0.05352  -0.0097   0.0515   1.0000
  13.250   1.2329   0.06397   0.05506  -0.0090   0.0510   1.0000
  13.500   1.2424   0.06543   0.05651  -0.0083   0.0505   1.0000
  13.750   1.2458   0.06785   0.05905  -0.0084   0.0502   1.0000
  14.000   1.2492   0.07028   0.06160  -0.0085   0.0499   1.0000
  14.250   1.2536   0.07260   0.06402  -0.0086   0.0495   1.0000
  14.500   1.2568   0.07509   0.06662  -0.0088   0.0490   1.0000
  14.750   1.2599   0.07763   0.06925  -0.0091   0.0486   1.0000
  15.000   1.2639   0.08002   0.07174  -0.0093   0.0482   1.0000
  15.250   1.2677   0.08245   0.07425  -0.0095   0.0477   1.0000
  15.500   1.2710   0.08500   0.07688  -0.0098   0.0474   1.0000
  15.750   1.2748   0.08746   0.07941  -0.0101   0.0470   1.0000
  16.000   1.2781   0.08998   0.08198  -0.0105   0.0464   1.0000
  16.250   1.2835   0.09213   0.08417  -0.0107   0.0459   1.0000
  16.500   1.2918   0.09373   0.08573  -0.0106   0.0452   1.0000
  16.750   1.2898   0.09725   0.08941  -0.0117   0.0450   1.0000
  17.000   1.2864   0.10105   0.09338  -0.0130   0.0446   1.0000
  17.250   1.2851   0.10452   0.09699  -0.0142   0.0442   1.0000
  17.500   1.2847   0.10786   0.10046  -0.0153   0.0439   1.0000
  17.750   1.2792   0.11217   0.10495  -0.0171   0.0431   1.0000
  18.000   1.2773   0.11583   0.10873  -0.0185   0.0427   1.0000
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