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AG45c -03f (ag45c03-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: AG45c -03f (ag45c03-il)
Reynolds number: 100,000
Max Cl/Cd: 47.95 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag45c03-il-100000-n5.txt
Download as CSV file: xf-ag45c03-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG45c -03f                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.5596   0.10543   0.10075   0.0206   1.0000   0.0471
  -7.250  -0.5610   0.10189   0.09729   0.0143   1.0000   0.0488
  -7.000  -0.5592   0.09788   0.09335   0.0080   1.0000   0.0492
  -6.750  -0.5509   0.09285   0.08833   0.0003   1.0000   0.0494
  -6.500  -0.4545   0.07505   0.07075   0.0009   1.0000   0.0355
  -6.250  -0.4535   0.07057   0.06631   0.0002   1.0000   0.0325
  -6.000  -0.4560   0.06451   0.06030  -0.0047   1.0000   0.0298
  -5.750  -0.5067   0.06778   0.06314  -0.0125   1.0000   0.0260
  -5.500  -0.4946   0.06325   0.05857  -0.0149   1.0000   0.0251
  -5.250  -0.4785   0.05797   0.05318  -0.0187   1.0000   0.0243
  -5.000  -0.4596   0.05229   0.04732  -0.0225   1.0000   0.0234
  -4.750  -0.4385   0.04642   0.04112  -0.0259   1.0000   0.0225
  -4.500  -0.4157   0.04068   0.03498  -0.0285   1.0000   0.0218
  -4.250  -0.3913   0.03546   0.02925  -0.0303   1.0000   0.0212
  -4.000  -0.3657   0.03107   0.02428  -0.0312   1.0000   0.0209
  -3.750  -0.3393   0.02761   0.02025  -0.0315   1.0000   0.0210
  -3.500  -0.3123   0.02487   0.01702  -0.0315   1.0000   0.0215
  -3.250  -0.2852   0.02297   0.01474  -0.0314   1.0000   0.0236
  -3.000  -0.2575   0.02134   0.01271  -0.0310   1.0000   0.0260
  -2.750  -0.2305   0.01940   0.01051  -0.0306   1.0000   0.0274
  -2.500  -0.2041   0.01791   0.00896  -0.0303   1.0000   0.0297
  -2.250  -0.1773   0.01686   0.00784  -0.0300   1.0000   0.0342
  -2.000  -0.1508   0.01583   0.00677  -0.0297   1.0000   0.0413
  -1.750  -0.1240   0.01492   0.00585  -0.0294   1.0000   0.0528
  -1.500  -0.0973   0.01404   0.00510  -0.0292   1.0000   0.0819
  -1.250  -0.0712   0.01315   0.00462  -0.0292   1.0000   0.1605
  -1.000  -0.0365   0.01222   0.00431  -0.0312   0.9654   0.3113
  -0.750  -0.0024   0.01098   0.00414  -0.0325   0.9114   0.6004
  -0.500   0.0305   0.01017   0.00395  -0.0312   0.8625   0.9190
  -0.250   0.0702   0.01020   0.00359  -0.0330   0.8193   1.0000
   0.000   0.0972   0.01036   0.00340  -0.0324   0.7884   1.0000
   0.250   0.1237   0.01054   0.00327  -0.0317   0.7644   1.0000
   0.500   0.1503   0.01073   0.00317  -0.0312   0.7445   1.0000
   0.750   0.1772   0.01092   0.00312  -0.0307   0.7270   1.0000
   1.000   0.2041   0.01112   0.00312  -0.0303   0.7108   1.0000
   1.250   0.2309   0.01132   0.00315  -0.0299   0.6947   1.0000
   1.500   0.2579   0.01148   0.00319  -0.0296   0.6780   1.0000
   1.750   0.2852   0.01162   0.00323  -0.0293   0.6606   1.0000
   2.000   0.3124   0.01175   0.00327  -0.0290   0.6433   1.0000
   2.250   0.3394   0.01189   0.00332  -0.0287   0.6260   1.0000
   2.500   0.3663   0.01203   0.00336  -0.0283   0.6088   1.0000
   2.750   0.3933   0.01217   0.00342  -0.0280   0.5908   1.0000
   3.000   0.4202   0.01232   0.00350  -0.0276   0.5721   1.0000
   3.250   0.4470   0.01249   0.00362  -0.0273   0.5535   1.0000
   3.500   0.4739   0.01267   0.00373  -0.0269   0.5342   1.0000
   3.750   0.5007   0.01287   0.00387  -0.0266   0.5141   1.0000
   4.000   0.5273   0.01309   0.00402  -0.0262   0.4943   1.0000
   4.250   0.5541   0.01331   0.00421  -0.0259   0.4731   1.0000
   4.500   0.5807   0.01357   0.00445  -0.0256   0.4522   1.0000
   4.750   0.6073   0.01383   0.00470  -0.0253   0.4299   1.0000
   5.000   0.6338   0.01412   0.00496  -0.0250   0.4075   1.0000
   5.250   0.6602   0.01443   0.00524  -0.0247   0.3843   1.0000
   5.500   0.6865   0.01476   0.00561  -0.0244   0.3601   1.0000
   5.750   0.7127   0.01513   0.00596  -0.0242   0.3357   1.0000
   6.000   0.7386   0.01554   0.00635  -0.0239   0.3113   1.0000
   6.250   0.7645   0.01599   0.00679  -0.0237   0.2860   1.0000
   6.500   0.7902   0.01648   0.00732  -0.0234   0.2610   1.0000
   6.750   0.8157   0.01702   0.00787  -0.0232   0.2363   1.0000
   7.000   0.8408   0.01762   0.00846  -0.0230   0.2129   1.0000
   7.250   0.8657   0.01827   0.00913  -0.0227   0.1901   1.0000
   7.500   0.8905   0.01897   0.00989  -0.0225   0.1684   1.0000
   7.750   0.9146   0.01975   0.01069  -0.0223   0.1485   1.0000
   8.000   0.9388   0.02057   0.01156  -0.0220   0.1291   1.0000
   8.250   0.9623   0.02147   0.01252  -0.0217   0.1116   1.0000
   8.500   0.9851   0.02249   0.01356  -0.0215   0.0952   1.0000
   8.750   1.0073   0.02361   0.01478  -0.0211   0.0810   1.0000
   9.000   1.0290   0.02482   0.01608  -0.0207   0.0679   1.0000
   9.250   1.0494   0.02621   0.01756  -0.0203   0.0576   1.0000
   9.500   1.0700   0.02755   0.01909  -0.0198   0.0485   1.0000
   9.750   1.0880   0.02934   0.02102  -0.0190   0.0427   1.0000
  10.000   1.1062   0.03092   0.02276  -0.0185   0.0369   1.0000
  10.250   1.1217   0.03301   0.02504  -0.0178   0.0331   1.0000
  10.500   1.1371   0.03518   0.02748  -0.0169   0.0302   1.0000
  10.750   1.1510   0.03718   0.02970  -0.0163   0.0274   1.0000
  11.000   1.1604   0.03983   0.03249  -0.0156   0.0251   1.0000
  11.250   1.1699   0.04256   0.03562  -0.0147   0.0235   1.0000
  11.500   1.1749   0.04574   0.03916  -0.0139   0.0224   1.0000
  11.750   1.1753   0.04916   0.04291  -0.0134   0.0216   1.0000
  12.000   1.1692   0.05272   0.04675  -0.0129   0.0211   1.0000
  12.250   1.1598   0.05689   0.05119  -0.0141   0.0207   1.0000
  12.500   1.1482   0.06193   0.05648  -0.0169   0.0205   1.0000
  12.750   1.1337   0.06789   0.06268  -0.0207   0.0204   1.0000
  13.000   1.1158   0.07496   0.06998  -0.0255   0.0205   1.0000
  13.250   1.0938   0.08342   0.07865  -0.0314   0.0209   1.0000
  13.500   1.0680   0.09332   0.08872  -0.0382   0.0214   1.0000
  13.750   1.0384   0.10486   0.10038  -0.0458   0.0221   1.0000
  14.000   1.0059   0.11802   0.11360  -0.0536   0.0230   1.0000
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