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Fage & Collins 1 (fg1-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Fage & Collins 1 (fg1-il)
Reynolds number: 100,000
Max Cl/Cd: 57.18 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fg1-il-100000.txt
Download as CSV file: xf-fg1-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Fage & Collins 1                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4269   0.10211   0.09705  -0.0298   1.0000   0.0769
  -8.750  -0.4451   0.10075   0.09580  -0.0313   1.0000   0.0772
  -8.500  -0.4576   0.09884   0.09392  -0.0339   1.0000   0.0775
  -8.250  -0.4276   0.09187   0.08698  -0.0261   1.0000   0.0804
  -8.000  -0.4272   0.08930   0.08446  -0.0242   1.0000   0.0824
  -7.750  -0.4312   0.08683   0.08205  -0.0233   1.0000   0.0844
  -7.500  -0.4368   0.08436   0.07963  -0.0229   1.0000   0.0866
  -7.250  -0.4436   0.08195   0.07725  -0.0233   1.0000   0.0890
  -7.000  -0.4567   0.08088   0.07598  -0.0286   1.0000   0.0919
  -6.750  -0.4561   0.07625   0.07141  -0.0273   1.0000   0.0931
  -6.500  -0.4504   0.07287   0.06816  -0.0234   1.0000   0.0950
  -6.250  -0.4461   0.07035   0.06566  -0.0212   1.0000   0.0980
  -6.000  -0.4412   0.06775   0.06302  -0.0209   1.0000   0.1026
  -5.750  -0.4356   0.06458   0.05957  -0.0238   1.0000   0.1089
  -5.500  -0.4293   0.06171   0.05683  -0.0207   1.0000   0.1125
  -5.250  -0.4177   0.06007   0.05475  -0.0228   1.0000   0.1239
  -5.000  -0.4105   0.05624   0.05115  -0.0202   1.0000   0.1267
  -4.750  -0.3994   0.05406   0.04893  -0.0189   1.0000   0.1342
  -4.500  -0.3879   0.05127   0.04601  -0.0186   1.0000   0.1431
  -4.250  -0.3743   0.04927   0.04379  -0.0184   1.0000   0.1568
  -4.000  -0.3624   0.04699   0.04158  -0.0165   1.0000   0.1656
  -3.750  -0.3494   0.04481   0.03933  -0.0154   1.0000   0.1796
  -3.500  -0.3356   0.04321   0.03753  -0.0147   1.0000   0.2044
  -3.250  -0.3234   0.04104   0.03544  -0.0129   1.0000   0.2227
  -3.000  -0.3121   0.03945   0.03386  -0.0109   1.0000   0.2541
  -2.750  -0.3020   0.03785   0.03235  -0.0084   1.0000   0.2882
  -2.500  -0.2929   0.03647   0.03103  -0.0055   1.0000   0.3327
  -2.250  -0.2822   0.03559   0.03016  -0.0027   1.0000   0.3776
  -2.000  -0.2755   0.03332   0.02813   0.0015   1.0000   0.4146
  -1.750  -0.2647   0.03209   0.02695   0.0046   1.0000   0.4556
  -1.500  -0.2449   0.03029   0.02524   0.0063   0.9967   0.4937
  -1.250  -0.1129   0.02823   0.01983  -0.0110   0.9891   0.1370
  -1.000  -0.0668   0.02684   0.01808  -0.0136   0.9807   0.1171
  -0.750  -0.0196   0.02646   0.01724  -0.0163   0.9714   0.1066
  -0.500   0.0255   0.02520   0.01591  -0.0193   0.9625   0.1004
  -0.250   0.0685   0.02453   0.01504  -0.0216   0.9519   0.0950
   0.000   0.1119   0.02422   0.01464  -0.0242   0.9409   0.0925
   0.250   0.1559   0.02353   0.01400  -0.0271   0.9305   0.0921
   0.500   0.2052   0.02265   0.01329  -0.0309   0.9221   0.0946
   0.750   0.2452   0.02213   0.01284  -0.0330   0.9094   0.0993
   1.000   0.2897   0.02170   0.01238  -0.0357   0.8969   0.1047
   1.250   0.3408   0.02112   0.01183  -0.0396   0.8845   0.1161
   1.500   0.4894   0.01791   0.01080  -0.0632   0.8827   1.0000
   1.750   0.5471   0.01706   0.00986  -0.0676   0.8681   1.0000
   2.000   0.6011   0.01631   0.00908  -0.0716   0.8518   1.0000
   2.250   0.6479   0.01565   0.00843  -0.0742   0.8331   1.0000
   2.500   0.6808   0.01523   0.00802  -0.0741   0.8078   1.0000
   2.750   0.7150   0.01481   0.00760  -0.0743   0.7790   1.0000
   3.000   0.7499   0.01445   0.00719  -0.0747   0.7439   1.0000
   3.250   0.7836   0.01426   0.00687  -0.0748   0.7008   1.0000
   3.500   0.8133   0.01434   0.00673  -0.0743   0.6528   1.0000
   3.750   0.8383   0.01466   0.00680  -0.0732   0.6052   1.0000
   4.000   0.8601   0.01515   0.00703  -0.0715   0.5611   1.0000
   4.250   0.8798   0.01576   0.00738  -0.0696   0.5190   1.0000
   4.500   0.8980   0.01644   0.00782  -0.0674   0.4781   1.0000
   4.750   0.9145   0.01712   0.00830  -0.0650   0.4376   1.0000
   5.000   0.9314   0.01782   0.00878  -0.0628   0.4017   1.0000
   5.250   0.9486   0.01852   0.00928  -0.0606   0.3702   1.0000
   5.500   0.9668   0.01920   0.00987  -0.0588   0.3438   1.0000
   5.750   0.9864   0.01992   0.01043  -0.0573   0.3230   1.0000
   6.000   1.0062   0.02061   0.01109  -0.0558   0.3042   1.0000
   6.250   1.0259   0.02129   0.01176  -0.0543   0.2873   1.0000
   6.500   1.0457   0.02199   0.01246  -0.0529   0.2716   1.0000
   6.750   1.0650   0.02272   0.01322  -0.0514   0.2560   1.0000
   7.000   1.0836   0.02348   0.01399  -0.0498   0.2403   1.0000
   7.250   1.1012   0.02427   0.01479  -0.0480   0.2237   1.0000
   7.500   1.1181   0.02514   0.01565  -0.0462   0.2069   1.0000
   7.750   1.1341   0.02609   0.01654  -0.0443   0.1894   1.0000
   8.000   1.1488   0.02713   0.01750  -0.0424   0.1718   1.0000
   8.250   1.1593   0.02795   0.01843  -0.0395   0.1549   1.0000
   8.500   1.1699   0.02883   0.01939  -0.0367   0.1391   1.0000
   8.750   1.1790   0.02965   0.02030  -0.0337   0.1242   1.0000
   9.000   1.1872   0.03052   0.02125  -0.0305   0.1101   1.0000
   9.250   1.1950   0.03162   0.02236  -0.0274   0.0973   1.0000
   9.500   1.2060   0.03321   0.02392  -0.0250   0.0871   1.0000
   9.750   1.2181   0.03491   0.02554  -0.0230   0.0782   1.0000
  10.000   1.2288   0.03691   0.02784  -0.0205   0.0718   1.0000
  10.250   1.2462   0.03918   0.03004  -0.0195   0.0667   1.0000
  10.500   1.2572   0.04198   0.03319  -0.0175   0.0637   1.0000
  10.750   1.2612   0.04413   0.03567  -0.0143   0.0608   1.0000
  11.000   1.2645   0.04613   0.03786  -0.0113   0.0583   1.0000
  11.250   1.2740   0.04860   0.04037  -0.0097   0.0560   1.0000
  11.500   1.2779   0.05291   0.04488  -0.0079   0.0547   1.0000
  11.750   1.2651   0.05547   0.04780  -0.0034   0.0544   1.0000
  12.000   1.2512   0.05841   0.05106   0.0004   0.0542   1.0000
  12.250   1.2334   0.06169   0.05464   0.0037   0.0541   1.0000
  12.500   1.2135   0.06538   0.05861   0.0062   0.0540   1.0000
  12.750   1.1912   0.06956   0.06306   0.0078   0.0540   1.0000
  13.000   1.1695   0.07421   0.06793   0.0083   0.0542   1.0000
  13.250   1.1446   0.07958   0.07351   0.0077   0.0543   1.0000
  13.500   1.1206   0.08562   0.07972   0.0060   0.0546   1.0000
  13.750   1.0940   0.09229   0.08660   0.0028   0.0550   1.0000
  14.000   0.7138   0.14146   0.13628  -0.0240   0.0885   1.0000
  14.250   0.7120   0.14577   0.14060  -0.0252   0.0891   1.0000
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