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Fage & Collins 3 (fg3-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: Fage & Collins 3 (fg3-il)
Reynolds number: 200,000
Max Cl/Cd: 65.31 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fg3-il-200000-n5.txt
Download as CSV file: xf-fg3-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3247   0.10882   0.10547  -0.0317   1.0000   0.0203
  -9.250  -0.3271   0.10627   0.10297  -0.0311   1.0000   0.0203
  -9.000  -0.3331   0.10398   0.10075  -0.0302   1.0000   0.0203
  -8.500  -0.3209   0.09636   0.09317  -0.0375   0.9948   0.0205
  -8.250  -0.3110   0.09199   0.08881  -0.0423   0.9901   0.0205
  -8.000  -0.3034   0.08766   0.08449  -0.0485   0.9831   0.0206
  -7.750  -0.2923   0.08274   0.07956  -0.0544   0.9758   0.0206
  -7.500  -0.2794   0.07797   0.07474  -0.0588   0.9689   0.0206
  -7.250  -0.2690   0.07357   0.07030  -0.0618   0.9618   0.0206
  -7.000  -0.2551   0.06943   0.06613  -0.0641   0.9572   0.0205
  -6.750  -0.2455   0.06558   0.06223  -0.0652   0.9511   0.0203
  -6.500  -0.2311   0.06202   0.05863  -0.0669   0.9460   0.0196
  -6.250  -0.2135   0.05739   0.05390  -0.0702   0.9398   0.0192
  -6.000  -0.1931   0.05284   0.04919  -0.0732   0.9331   0.0190
  -5.500  -0.1428   0.04525   0.04123  -0.0783   0.9202   0.0238
  -5.250  -0.1132   0.04014   0.03578  -0.0811   0.9159   0.0230
  -5.000  -0.0908   0.03649   0.03183  -0.0813   0.9084   0.0232
  -4.750  -0.0567   0.03271   0.02752  -0.0827   0.9031   0.0261
  -4.250  -0.0036   0.02693   0.02099  -0.0833   0.8884   0.0282
  -4.000   0.0208   0.02589   0.01985  -0.0833   0.8803   0.0310
  -3.750   0.0483   0.02385   0.01742  -0.0830   0.8735   0.0319
  -3.500   0.0681   0.02227   0.01552  -0.0810   0.8651   0.0321
  -3.250   0.0975   0.02107   0.01393  -0.0809   0.8582   0.0339
  -3.000   0.1173   0.02066   0.01323  -0.0786   0.8485   0.0352
  -2.750   0.1424   0.01929   0.01161  -0.0779   0.8400   0.0353
  -2.500   0.1674   0.01799   0.01010  -0.0771   0.8300   0.0356
  -2.250   0.1894   0.01690   0.00889  -0.0757   0.8184   0.0364
  -2.000   0.2131   0.01613   0.00806  -0.0748   0.8058   0.0382
  -1.750   0.2388   0.01545   0.00726  -0.0741   0.7912   0.0384
  -1.500   0.2659   0.01482   0.00651  -0.0737   0.7747   0.0384
  -1.250   0.2938   0.01424   0.00582  -0.0734   0.7546   0.0387
  -1.000   0.3204   0.01378   0.00524  -0.0729   0.7299   0.0391
  -0.750   0.3459   0.01343   0.00474  -0.0722   0.6998   0.0396
  -0.500   0.3686   0.01321   0.00433  -0.0709   0.6630   0.0401
  -0.250   0.3883   0.01314   0.00404  -0.0690   0.6190   0.0420
   0.000   0.4053   0.01319   0.00384  -0.0666   0.5734   0.0434
   0.250   0.4214   0.01327   0.00367  -0.0641   0.5347   0.0437
   0.500   0.4381   0.01338   0.00356  -0.0617   0.5032   0.0439
   0.750   0.4565   0.01347   0.00347  -0.0597   0.4790   0.0442
   1.000   0.4755   0.01358   0.00341  -0.0579   0.4590   0.0446
   1.250   0.4955   0.01368   0.00337  -0.0562   0.4428   0.0452
   1.750   0.5370   0.01389   0.00337  -0.0533   0.4161   0.0482
   2.000   0.5581   0.01400   0.00341  -0.0520   0.4049   0.0521
   2.250   0.7479   0.01293   0.00432  -0.0897   0.3778   1.0000
   2.500   0.7695   0.01313   0.00445  -0.0885   0.3701   1.0000
   2.750   0.7909   0.01335   0.00460  -0.0873   0.3637   1.0000
   3.000   0.8129   0.01356   0.00476  -0.0862   0.3570   1.0000
   3.250   0.8341   0.01380   0.00493  -0.0850   0.3513   1.0000
   3.500   0.8563   0.01401   0.00513  -0.0839   0.3454   1.0000
   3.750   0.8779   0.01424   0.00532  -0.0828   0.3395   1.0000
   4.000   0.8992   0.01450   0.00554  -0.0816   0.3347   1.0000
   4.250   0.9215   0.01471   0.00577  -0.0807   0.3295   1.0000
   4.500   0.9433   0.01496   0.00602  -0.0796   0.3251   1.0000
   4.750   0.9645   0.01525   0.00628  -0.0784   0.3212   1.0000
   5.000   0.9869   0.01549   0.00656  -0.0775   0.3172   1.0000
   5.250   1.0090   0.01574   0.00686  -0.0765   0.3130   1.0000
   5.500   1.0306   0.01603   0.00717  -0.0755   0.3094   1.0000
   5.750   1.0519   0.01636   0.00749  -0.0744   0.3060   1.0000
   6.000   1.0741   0.01661   0.00784  -0.0735   0.3021   1.0000
   6.250   1.0958   0.01689   0.00821  -0.0725   0.2981   1.0000
   6.500   1.1153   0.01719   0.00851  -0.0711   0.2923   1.0000
   6.750   1.1337   0.01739   0.00880  -0.0695   0.2824   1.0000
   7.000   1.1508   0.01764   0.00907  -0.0676   0.2723   1.0000
   7.250   1.1693   0.01791   0.00940  -0.0660   0.2646   1.0000
   7.500   1.1867   0.01817   0.00975  -0.0642   0.2538   1.0000
   7.750   1.2020   0.01846   0.01007  -0.0620   0.2403   1.0000
   8.000   1.2147   0.01881   0.01040  -0.0594   0.2207   1.0000
   8.250   1.2233   0.01941   0.01084  -0.0561   0.1814   1.0000
   8.500   1.2029   0.02212   0.01261  -0.0488   0.0543   1.0000
   8.750   1.2023   0.02362   0.01398  -0.0445   0.0257   1.0000
   9.000   1.2109   0.02453   0.01499  -0.0416   0.0211   1.0000
   9.250   1.2202   0.02540   0.01600  -0.0390   0.0191   1.0000
   9.500   1.2282   0.02636   0.01711  -0.0363   0.0179   1.0000
   9.750   1.2316   0.02765   0.01856  -0.0331   0.0162   1.0000
  10.000   1.2336   0.02906   0.02015  -0.0300   0.0154   1.0000
  10.250   1.2351   0.03053   0.02179  -0.0271   0.0144   1.0000
  10.500   1.2384   0.03195   0.02335  -0.0246   0.0138   1.0000
  10.750   1.2372   0.03376   0.02533  -0.0220   0.0131   1.0000
  11.000   1.2353   0.03573   0.02745  -0.0197   0.0130   1.0000
  11.250   1.2314   0.03800   0.02988  -0.0175   0.0125   1.0000
  11.500   1.2257   0.04060   0.03264  -0.0157   0.0123   1.0000
  11.750   1.2187   0.04354   0.03571  -0.0143   0.0120   1.0000
  12.000   1.2112   0.04678   0.03908  -0.0134   0.0118   1.0000
  12.250   1.2027   0.05038   0.04281  -0.0129   0.0115   1.0000
  12.500   1.1957   0.05404   0.04660  -0.0128   0.0115   1.0000
  12.750   1.1889   0.05785   0.05051  -0.0131   0.0112   1.0000
  13.000   1.1806   0.06200   0.05476  -0.0135   0.0109   1.0000
  13.250   1.1756   0.06575   0.05861  -0.0138   0.0109   1.0000
  13.500   1.1703   0.06954   0.06249  -0.0142   0.0107   1.0000
  13.750   1.1620   0.07330   0.06625  -0.0138   0.0101   1.0000
  14.000   1.1621   0.07634   0.06937  -0.0139   0.0099   1.0000
  14.250   1.1624   0.07967   0.07285  -0.0146   0.0095   1.0000
  14.500   1.1640   0.08246   0.07575  -0.0144   0.0093   1.0000
  14.750   1.1658   0.08524   0.07864  -0.0142   0.0091   1.0000
  15.000   1.1673   0.08814   0.08164  -0.0142   0.0088   1.0000
  15.250   1.1695   0.09090   0.08452  -0.0140   0.0087   1.0000
  15.500   1.1711   0.09384   0.08758  -0.0140   0.0086   1.0000
  15.750   1.1719   0.09698   0.09086  -0.0140   0.0085   1.0000
  16.000   1.1708   0.10057   0.09459  -0.0148   0.0083   1.0000
  16.250   1.1682   0.10443   0.09860  -0.0155   0.0081   1.0000
  16.500   1.1654   0.10840   0.10272  -0.0165   0.0081   1.0000
  16.750   1.1617   0.11259   0.10704  -0.0181   0.0078   1.0000
  17.000   1.1564   0.11718   0.11179  -0.0196   0.0078   1.0000
  17.250   1.1513   0.12180   0.11655  -0.0214   0.0077   1.0000
  17.500   1.1440   0.12694   0.12185  -0.0236   0.0077   1.0000
  17.750   1.1398   0.13140   0.12642  -0.0257   0.0075   1.0000
  18.000   1.1333   0.13647   0.13159  -0.0282   0.0073   1.0000
  18.250   1.1254   0.14202   0.13730  -0.0310   0.0072   1.0000
  18.500   1.1190   0.14727   0.14265  -0.0337   0.0071   1.0000
  18.750   1.1050   0.15486   0.15047  -0.0378   0.0073   1.0000
  19.000   1.1032   0.15878   0.15439  -0.0400   0.0069   1.0000
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