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AG18 (ag18-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: AG18 (ag18-il)
Reynolds number: 200,000
Max Cl/Cd: 60.34 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag18-il-200000-n5.txt
Download as CSV file: xf-ag18-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG18                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4322   0.08737   0.08409   0.0008   1.0000   0.0153
  -8.000  -0.4304   0.08331   0.08005   0.0002   1.0000   0.0142
  -7.500  -0.5220   0.08831   0.08493   0.0056   1.0000   0.0148
  -7.250  -0.5166   0.08412   0.08078   0.0027   1.0000   0.0135
  -6.750  -0.4918   0.06916   0.06585  -0.0144   1.0000   0.0103
  -6.250  -0.4511   0.05743   0.05399  -0.0276   1.0000   0.0098
  -6.000  -0.4278   0.04991   0.04632  -0.0351   1.0000   0.0097
  -5.750  -0.4021   0.04183   0.03795  -0.0415   1.0000   0.0097
  -5.500  -0.3758   0.03330   0.02886  -0.0469   1.0000   0.0104
  -5.250  -0.3528   0.03229   0.02775  -0.0480   1.0000   0.0120
  -5.000  -0.3260   0.02828   0.02331  -0.0496   1.0000   0.0129
  -4.750  -0.2979   0.02363   0.01799  -0.0507   1.0000   0.0126
  -4.500  -0.2700   0.02043   0.01420  -0.0511   1.0000   0.0126
  -4.250  -0.2425   0.01814   0.01147  -0.0510   1.0000   0.0128
  -4.000  -0.2154   0.01639   0.00936  -0.0507   1.0000   0.0132
  -3.750  -0.1886   0.01500   0.00774  -0.0503   1.0000   0.0140
  -3.500  -0.1619   0.01386   0.00644  -0.0499   1.0000   0.0151
  -3.250  -0.1354   0.01310   0.00557  -0.0495   1.0000   0.0168
  -3.000  -0.1090   0.01225   0.00469  -0.0493   1.0000   0.0221
  -2.750  -0.0823   0.01165   0.00396  -0.0490   1.0000   0.0265
  -2.500  -0.0555   0.01101   0.00333  -0.0488   1.0000   0.0425
  -2.250  -0.0289   0.01051   0.00295  -0.0486   1.0000   0.0774
  -2.000  -0.0024   0.01004   0.00273  -0.0486   1.0000   0.1361
  -1.750   0.0315   0.00956   0.00256  -0.0502   0.9945   0.2265
  -1.500   0.0688   0.00910   0.00244  -0.0525   0.9830   0.3346
  -1.250   0.1051   0.00870   0.00233  -0.0544   0.9690   0.4350
  -1.000   0.1394   0.00830   0.00225  -0.0557   0.9517   0.5390
  -0.750   0.1710   0.00781   0.00217  -0.0561   0.9315   0.6679
  -0.500   0.2023   0.00709   0.00200  -0.0557   0.9087   1.0000
  -0.250   0.2328   0.00712   0.00189  -0.0558   0.8817   1.0000
   0.000   0.2608   0.00719   0.00180  -0.0554   0.8525   1.0000
   0.250   0.2875   0.00728   0.00173  -0.0547   0.8218   1.0000
   0.500   0.3136   0.00741   0.00169  -0.0539   0.7904   1.0000
   0.750   0.3397   0.00756   0.00167  -0.0531   0.7579   1.0000
   1.000   0.3657   0.00773   0.00166  -0.0524   0.7244   1.0000
   1.250   0.3919   0.00792   0.00168  -0.0517   0.6896   1.0000
   1.500   0.4181   0.00814   0.00171  -0.0511   0.6531   1.0000
   1.750   0.4443   0.00837   0.00179  -0.0506   0.6141   1.0000
   2.000   0.4705   0.00863   0.00186  -0.0501   0.5732   1.0000
   2.250   0.4967   0.00892   0.00196  -0.0496   0.5313   1.0000
   2.500   0.5230   0.00923   0.00208  -0.0492   0.4892   1.0000
   2.750   0.5492   0.00955   0.00223  -0.0489   0.4479   1.0000
   3.000   0.5756   0.00989   0.00245  -0.0486   0.4084   1.0000
   3.250   0.6020   0.01024   0.00265  -0.0483   0.3707   1.0000
   3.500   0.6283   0.01061   0.00289  -0.0481   0.3354   1.0000
   3.750   0.6547   0.01097   0.00314  -0.0478   0.3027   1.0000
   4.000   0.6810   0.01136   0.00342  -0.0476   0.2720   1.0000
   4.250   0.7073   0.01175   0.00377  -0.0474   0.2429   1.0000
   4.500   0.7336   0.01216   0.00411  -0.0472   0.2158   1.0000
   4.750   0.7597   0.01259   0.00448  -0.0470   0.1889   1.0000
   5.000   0.7858   0.01304   0.00488  -0.0467   0.1649   1.0000
   5.250   0.8117   0.01351   0.00531  -0.0465   0.1414   1.0000
   5.500   0.8374   0.01403   0.00584  -0.0462   0.1207   1.0000
   5.750   0.8631   0.01456   0.00637  -0.0460   0.1019   1.0000
   6.000   0.8883   0.01518   0.00694  -0.0457   0.0842   1.0000
   6.250   0.9135   0.01580   0.00758  -0.0453   0.0702   1.0000
   6.500   0.9385   0.01645   0.00826  -0.0450   0.0564   1.0000
   6.750   0.9630   0.01722   0.00906  -0.0446   0.0454   1.0000
   7.000   0.9871   0.01806   0.00997  -0.0441   0.0348   1.0000
   7.250   1.0113   0.01888   0.01093  -0.0436   0.0276   1.0000
   7.500   1.0345   0.01989   0.01205  -0.0431   0.0213   1.0000
   7.750   1.0569   0.02109   0.01337  -0.0424   0.0172   1.0000
   8.000   1.0780   0.02254   0.01500  -0.0416   0.0142   1.0000
   8.250   1.1004   0.02358   0.01620  -0.0410   0.0115   1.0000
   8.500   1.1203   0.02515   0.01796  -0.0402   0.0101   1.0000
   8.750   1.1354   0.02778   0.02083  -0.0389   0.0091   1.0000
   9.000   1.1530   0.02983   0.02325  -0.0378   0.0086   1.0000
   9.250   1.1682   0.03230   0.02606  -0.0366   0.0082   1.0000
   9.500   1.1807   0.03516   0.02932  -0.0353   0.0078   1.0000
   9.750   1.1907   0.03817   0.03271  -0.0340   0.0074   1.0000
  10.000   1.1993   0.04086   0.03574  -0.0328   0.0069   1.0000
  10.250   1.2069   0.04318   0.03832  -0.0319   0.0063   1.0000
  10.500   1.2122   0.04539   0.04073  -0.0310   0.0059   1.0000
  10.750   1.2099   0.04814   0.04368  -0.0299   0.0057   1.0000
  11.000   1.1987   0.05174   0.04751  -0.0292   0.0055   1.0000
  11.250   1.1841   0.05656   0.05257  -0.0309   0.0055   1.0000
  11.500   1.1684   0.06291   0.05917  -0.0352   0.0055   1.0000
  11.750   1.1496   0.07156   0.06808  -0.0421   0.0056   1.0000
  12.000   1.0791   0.09558   0.09256  -0.0590   0.0072   1.0000
  12.250   1.0448   0.10982   0.10686  -0.0670   0.0079   1.0000
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