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AG16 (ag16-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: AG16 (ag16-il)
Reynolds number: 200,000
Max Cl/Cd: 60.33 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag16-il-200000-n5.txt
Download as CSV file: xf-ag16-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG16                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5700   0.10614   0.10265   0.0140   1.0000   0.0116
  -9.000  -0.5697   0.10101   0.09755   0.0115   1.0000   0.0110
  -8.500  -0.5735   0.08836   0.08500   0.0046   1.0000   0.0097
  -8.000  -0.5695   0.07876   0.07546  -0.0017   1.0000   0.0094
  -7.750  -0.5675   0.07282   0.06956  -0.0075   1.0000   0.0093
  -7.500  -0.5606   0.06503   0.06179  -0.0166   1.0000   0.0092
  -7.250  -0.5485   0.05301   0.04964  -0.0303   1.0000   0.0090
  -7.000  -0.5361   0.04134   0.03747  -0.0406   1.0000   0.0088
  -6.750  -0.5187   0.03385   0.02931  -0.0453   1.0000   0.0089
  -6.500  -0.4971   0.02883   0.02360  -0.0473   1.0000   0.0091
  -6.250  -0.4728   0.02574   0.01994  -0.0480   1.0000   0.0094
  -6.000  -0.4497   0.02287   0.01675  -0.0488   1.0000   0.0107
  -5.750  -0.4243   0.02175   0.01543  -0.0489   1.0000   0.0121
  -5.500  -0.3984   0.01978   0.01311  -0.0488   1.0000   0.0128
  -5.250  -0.3723   0.01801   0.01100  -0.0485   1.0000   0.0133
  -5.000  -0.3462   0.01656   0.00934  -0.0482   1.0000   0.0141
  -4.750  -0.3200   0.01541   0.00802  -0.0479   1.0000   0.0150
  -4.500  -0.2938   0.01415   0.00662  -0.0476   1.0000   0.0167
  -4.250  -0.2676   0.01348   0.00590  -0.0474   1.0000   0.0209
  -4.000  -0.2410   0.01277   0.00508  -0.0472   1.0000   0.0257
  -3.750  -0.2145   0.01212   0.00439  -0.0469   1.0000   0.0362
  -3.500  -0.1882   0.01152   0.00384  -0.0467   1.0000   0.0612
  -3.250  -0.1620   0.01099   0.00348  -0.0466   1.0000   0.1008
  -3.000  -0.1358   0.01052   0.00322  -0.0466   1.0000   0.1520
  -2.750  -0.1096   0.01015   0.00303  -0.0465   1.0000   0.2046
  -2.500  -0.0834   0.00987   0.00288  -0.0463   1.0000   0.2523
  -2.250  -0.0469   0.00960   0.00271  -0.0483   0.9918   0.3001
  -2.000  -0.0098   0.00935   0.00258  -0.0503   0.9811   0.3505
  -1.750   0.0263   0.00911   0.00248  -0.0521   0.9685   0.4033
  -1.500   0.0613   0.00888   0.00238  -0.0535   0.9536   0.4536
  -1.250   0.0948   0.00867   0.00230  -0.0545   0.9355   0.5039
  -1.000   0.1270   0.00847   0.00223  -0.0552   0.9151   0.5559
  -0.750   0.1563   0.00826   0.00217  -0.0551   0.8911   0.6109
  -0.500   0.1830   0.00805   0.00210  -0.0543   0.8650   0.6740
  -0.250   0.2063   0.00780   0.00205  -0.0526   0.8372   0.7552
   0.000   0.2307   0.00746   0.00195  -0.0507   0.8087   0.9172
   0.250   0.2613   0.00752   0.00185  -0.0509   0.7778   1.0000
   0.500   0.2878   0.00766   0.00182  -0.0503   0.7475   1.0000
   0.750   0.3143   0.00782   0.00181  -0.0498   0.7168   1.0000
   1.000   0.3410   0.00799   0.00181  -0.0493   0.6864   1.0000
   1.250   0.3677   0.00817   0.00184  -0.0488   0.6561   1.0000
   1.500   0.3945   0.00837   0.00190  -0.0484   0.6258   1.0000
   1.750   0.4213   0.00858   0.00196  -0.0481   0.5959   1.0000
   2.000   0.4482   0.00880   0.00205  -0.0477   0.5655   1.0000
   2.250   0.4750   0.00903   0.00215  -0.0474   0.5349   1.0000
   2.500   0.5019   0.00927   0.00227  -0.0471   0.5046   1.0000
   2.750   0.5287   0.00953   0.00244  -0.0469   0.4743   1.0000
   3.000   0.5554   0.00981   0.00260  -0.0466   0.4437   1.0000
   3.250   0.5822   0.01009   0.00279  -0.0464   0.4129   1.0000
   3.500   0.6089   0.01039   0.00300  -0.0461   0.3821   1.0000
   3.750   0.6355   0.01073   0.00326  -0.0459   0.3510   1.0000
   4.000   0.6620   0.01108   0.00352  -0.0457   0.3198   1.0000
   4.250   0.6884   0.01145   0.00381  -0.0455   0.2886   1.0000
   4.500   0.7147   0.01185   0.00413  -0.0453   0.2578   1.0000
   4.750   0.7409   0.01228   0.00447  -0.0451   0.2284   1.0000
   5.000   0.7670   0.01274   0.00489  -0.0449   0.2000   1.0000
   5.250   0.7928   0.01323   0.00531  -0.0446   0.1720   1.0000
   5.500   0.8185   0.01376   0.00577  -0.0444   0.1446   1.0000
   5.750   0.8442   0.01430   0.00628  -0.0441   0.1202   1.0000
   6.000   0.8694   0.01492   0.00684  -0.0439   0.0952   1.0000
   6.250   0.8943   0.01560   0.00751  -0.0436   0.0736   1.0000
   6.500   0.9188   0.01638   0.00823  -0.0432   0.0548   1.0000
   6.750   0.9430   0.01721   0.00906  -0.0428   0.0420   1.0000
   7.000   0.9668   0.01812   0.00998  -0.0423   0.0310   1.0000
   7.250   0.9908   0.01896   0.01094  -0.0418   0.0239   1.0000
   7.500   1.0136   0.02005   0.01214  -0.0412   0.0187   1.0000
   7.750   1.0360   0.02117   0.01340  -0.0405   0.0154   1.0000
   8.000   1.0563   0.02268   0.01505  -0.0397   0.0127   1.0000
   8.250   1.0783   0.02374   0.01633  -0.0390   0.0107   1.0000
   8.500   1.0985   0.02514   0.01790  -0.0382   0.0096   1.0000
   8.750   1.1171   0.02676   0.01969  -0.0373   0.0087   1.0000
   9.000   1.1313   0.02924   0.02240  -0.0360   0.0081   1.0000
   9.250   1.1458   0.03166   0.02509  -0.0347   0.0078   1.0000
   9.500   1.1598   0.03405   0.02780  -0.0335   0.0075   1.0000
   9.750   1.1708   0.03680   0.03090  -0.0321   0.0073   1.0000
  10.000   1.1779   0.03990   0.03437  -0.0306   0.0071   1.0000
  10.250   1.1802   0.04330   0.03815  -0.0291   0.0070   1.0000
  10.500   1.1767   0.04694   0.04215  -0.0277   0.0070   1.0000
  10.750   1.1655   0.05058   0.04609  -0.0261   0.0069   1.0000
  11.000   1.1512   0.05489   0.05067  -0.0263   0.0069   1.0000
  11.250   1.1356   0.06024   0.05627  -0.0289   0.0069   1.0000
  11.500   1.1193   0.06685   0.06311  -0.0335   0.0070   1.0000
  11.750   1.1019   0.07476   0.07122  -0.0397   0.0070   1.0000
  12.000   1.0832   0.08384   0.08047  -0.0466   0.0071   1.0000
  12.250   1.0629   0.09379   0.09054  -0.0535   0.0072   1.0000
  12.500   1.0410   0.10444   0.10129  -0.0601   0.0073   1.0000
  12.750   1.0175   0.11569   0.11259  -0.0663   0.0075   1.0000
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