Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

AG04 (ag04-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: AG04 (ag04-il)
Reynolds number: 1,000,000
Max Cl/Cd: 85.04 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag04-il-1000000-n5.txt
Download as CSV file: xf-ag04-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG04                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.6097   0.11516   0.11356   0.0278   1.0000   0.0035
  -9.500  -0.6103   0.10983   0.10825   0.0257   1.0000   0.0032
  -8.000  -0.6864   0.02337   0.02038  -0.0368   1.0000   0.0024
  -7.750  -0.6651   0.02016   0.01673  -0.0372   1.0000   0.0025
  -7.500  -0.6412   0.01828   0.01455  -0.0372   1.0000   0.0026
  -7.250  -0.6161   0.01700   0.01305  -0.0371   1.0000   0.0026
  -7.000  -0.5928   0.01440   0.01001  -0.0370   1.0000   0.0030
  -6.750  -0.5666   0.01366   0.00917  -0.0369   1.0000   0.0032
  -6.500  -0.5402   0.01301   0.00841  -0.0368   1.0000   0.0033
  -6.250  -0.5136   0.01239   0.00768  -0.0366   1.0000   0.0035
  -6.000  -0.4870   0.01179   0.00698  -0.0364   1.0000   0.0037
  -5.750  -0.4603   0.01116   0.00624  -0.0362   1.0000   0.0039
  -5.500  -0.4335   0.01058   0.00557  -0.0360   1.0000   0.0041
  -5.250  -0.4067   0.01007   0.00498  -0.0358   1.0000   0.0042
  -5.000  -0.3798   0.00962   0.00446  -0.0355   1.0000   0.0044
  -4.750  -0.3529   0.00931   0.00411  -0.0353   1.0000   0.0047
  -4.500  -0.3247   0.00882   0.00353  -0.0353   0.9981   0.0050
  -4.250  -0.2916   0.00834   0.00297  -0.0365   0.9882   0.0057
  -4.000  -0.2578   0.00800   0.00261  -0.0377   0.9743   0.0066
  -3.750  -0.2253   0.00775   0.00230  -0.0386   0.9558   0.0076
  -3.500  -0.1974   0.00753   0.00201  -0.0383   0.9312   0.0103
  -3.250  -0.1715   0.00739   0.00179  -0.0376   0.9035   0.0141
  -3.000  -0.1457   0.00727   0.00160  -0.0370   0.8736   0.0215
  -2.750  -0.1194   0.00713   0.00143  -0.0365   0.8427   0.0353
  -2.500  -0.0927   0.00704   0.00128  -0.0361   0.8106   0.0515
  -2.250  -0.0657   0.00696   0.00114  -0.0358   0.7778   0.0722
  -2.000  -0.0385   0.00691   0.00103  -0.0356   0.7459   0.0914
  -1.750  -0.0110   0.00685   0.00093  -0.0355   0.7154   0.1155
  -1.500   0.0165   0.00679   0.00085  -0.0354   0.6868   0.1438
  -1.250   0.0442   0.00674   0.00078  -0.0353   0.6574   0.1731
  -1.000   0.0719   0.00670   0.00072  -0.0352   0.6290   0.2038
  -0.750   0.0996   0.00665   0.00068  -0.0352   0.6006   0.2425
  -0.500   0.1273   0.00661   0.00066  -0.0351   0.5725   0.2808
  -0.250   0.1550   0.00656   0.00064  -0.0351   0.5442   0.3270
   0.000   0.1827   0.00652   0.00064  -0.0351   0.5159   0.3757
   0.250   0.2103   0.00647   0.00065  -0.0351   0.4871   0.4332
   0.750   0.2653   0.00635   0.00071  -0.0351   0.4316   0.5676
   1.000   0.2922   0.00619   0.00075  -0.0350   0.4045   0.6689
   1.250   0.3141   0.00567   0.00082  -0.0335   0.3809   0.8800
   1.500   0.3462   0.00564   0.00085  -0.0342   0.3550   1.0000
   1.750   0.3739   0.00581   0.00091  -0.0342   0.3304   1.0000
   2.000   0.4016   0.00597   0.00098  -0.0341   0.3082   1.0000
   2.250   0.4293   0.00614   0.00105  -0.0340   0.2853   1.0000
   2.500   0.4569   0.00633   0.00114  -0.0340   0.2630   1.0000
   2.750   0.4845   0.00651   0.00125  -0.0339   0.2425   1.0000
   3.000   0.5120   0.00671   0.00136  -0.0338   0.2205   1.0000
   3.250   0.5396   0.00690   0.00147  -0.0337   0.2019   1.0000
   3.500   0.5670   0.00712   0.00160  -0.0337   0.1813   1.0000
   3.750   0.5944   0.00733   0.00176  -0.0336   0.1646   1.0000
   4.000   0.6218   0.00755   0.00192  -0.0335   0.1457   1.0000
   4.250   0.6491   0.00779   0.00209  -0.0334   0.1291   1.0000
   4.500   0.6762   0.00806   0.00228  -0.0333   0.1114   1.0000
   4.750   0.7034   0.00831   0.00249  -0.0332   0.0969   1.0000
   5.000   0.7304   0.00860   0.00272  -0.0331   0.0804   1.0000
   5.250   0.7572   0.00891   0.00297  -0.0330   0.0654   1.0000
   5.500   0.7841   0.00922   0.00323  -0.0328   0.0535   1.0000
   5.750   0.8108   0.00954   0.00351  -0.0327   0.0432   1.0000
   6.000   0.8375   0.00987   0.00383  -0.0325   0.0344   1.0000
   6.250   0.8640   0.01022   0.00415  -0.0324   0.0266   1.0000
   6.500   0.8903   0.01060   0.00450  -0.0322   0.0203   1.0000
   6.750   0.9168   0.01094   0.00485  -0.0320   0.0160   1.0000
   7.000   0.9429   0.01136   0.00526  -0.0318   0.0118   1.0000
   7.250   0.9691   0.01171   0.00564  -0.0316   0.0101   1.0000
   7.500   0.9949   0.01216   0.00612  -0.0313   0.0079   1.0000
   7.750   1.0208   0.01257   0.00658  -0.0311   0.0067   1.0000
   8.000   1.0465   0.01301   0.00706  -0.0308   0.0056   1.0000
   8.250   1.0714   0.01360   0.00769  -0.0305   0.0044   1.0000
   8.500   1.0968   0.01406   0.00821  -0.0302   0.0039   1.0000
   8.750   1.1218   0.01456   0.00877  -0.0299   0.0034   1.0000
   9.000   1.1464   0.01513   0.00940  -0.0295   0.0030   1.0000
   9.250   1.1703   0.01584   0.01020  -0.0291   0.0026   1.0000
   9.500   1.1933   0.01671   0.01119  -0.0286   0.0023   1.0000
   9.750   1.2170   0.01738   0.01196  -0.0281   0.0023   1.0000
  10.000   1.2401   0.01811   0.01279  -0.0276   0.0022   1.0000
  10.250   1.2627   0.01890   0.01369  -0.0271   0.0021   1.0000
  10.500   1.2847   0.01976   0.01467  -0.0266   0.0020   1.0000
  10.750   1.3061   0.02067   0.01569  -0.0260   0.0019   1.0000
  11.000   1.3268   0.02163   0.01678  -0.0253   0.0018   1.0000
  11.250   1.3469   0.02265   0.01794  -0.0246   0.0017   1.0000
  11.500   1.3662   0.02370   0.01913  -0.0239   0.0016   1.0000
  11.750   1.3845   0.02484   0.02039  -0.0231   0.0015   1.0000
  12.000   1.4014   0.02609   0.02177  -0.0222   0.0014   1.0000
  12.250   1.4163   0.02752   0.02335  -0.0212   0.0013   1.0000
  12.500   1.4278   0.02926   0.02527  -0.0200   0.0013   1.0000
  12.750   1.4334   0.03153   0.02775  -0.0185   0.0012   1.0000
  13.000   1.4274   0.03458   0.03107  -0.0163   0.0011   1.0000
  13.250   1.4130   0.03785   0.03457  -0.0141   0.0011   1.0000
  13.500   1.3987   0.04205   0.03897  -0.0147   0.0011   1.0000
  13.750   1.3865   0.04733   0.04443  -0.0178   0.0011   1.0000
  14.000   1.3686   0.05507   0.05239  -0.0238   0.0011   1.0000
  14.500   1.3283   0.07332   0.07096  -0.0366   0.0011   1.0000
  14.750   1.3038   0.08291   0.08066  -0.0419   0.0011   1.0000
  15.000   1.2794   0.09214   0.08998  -0.0465   0.0012   1.0000
  15.250   1.2500   0.10225   0.10019  -0.0514   0.0012   1.0000
  15.500   1.2169   0.11317   0.11120  -0.0566   0.0013   1.0000
  15.750   1.1814   0.12491   0.12303  -0.0623   0.0014   1.0000
<< Back to AG04 (ag04-il)

Polar data table (+)

Polar graphs


<< Back to AG04 (ag04-il)