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AG37 (ag37-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: AG37 (ag37-il)
Reynolds number: 100,000
Max Cl/Cd: 49.78 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag37-il-100000-n5.txt
Download as CSV file: xf-ag37-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG37                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5109   0.10416   0.09917  -0.0050   1.0000   0.0520
  -9.750  -0.5147   0.10050   0.09559  -0.0106   1.0000   0.0527
  -9.500  -0.5160   0.09645   0.09159  -0.0157   1.0000   0.0530
  -9.250  -0.5122   0.09152   0.08667  -0.0221   1.0000   0.0531
  -8.250  -0.4834   0.06785   0.06290  -0.0300   1.0000   0.0299
  -8.000  -0.4744   0.06346   0.05847  -0.0320   1.0000   0.0291
  -7.750  -0.4636   0.05853   0.05342  -0.0344   1.0000   0.0282
  -7.500  -0.4511   0.05332   0.04801  -0.0368   1.0000   0.0274
  -7.250  -0.4367   0.04800   0.04242  -0.0386   1.0000   0.0267
  -7.000  -0.4206   0.04279   0.03684  -0.0398   1.0000   0.0261
  -6.750  -0.4026   0.03817   0.03179  -0.0402   1.0000   0.0258
  -6.500  -0.3828   0.03448   0.02766  -0.0401   1.0000   0.0263
  -6.250  -0.3614   0.03153   0.02425  -0.0398   1.0000   0.0279
  -6.000  -0.3387   0.02872   0.02089  -0.0392   1.0000   0.0292
  -5.750  -0.3151   0.02619   0.01787  -0.0384   1.0000   0.0297
  -5.500  -0.2909   0.02413   0.01536  -0.0376   1.0000   0.0304
  -5.250  -0.2666   0.02220   0.01311  -0.0368   1.0000   0.0313
  -5.000  -0.2431   0.02088   0.01173  -0.0362   1.0000   0.0338
  -4.750  -0.2189   0.01989   0.01061  -0.0354   1.0000   0.0373
  -4.500  -0.1942   0.01876   0.00932  -0.0346   1.0000   0.0395
  -4.250  -0.1697   0.01769   0.00815  -0.0338   1.0000   0.0420
  -4.000  -0.1457   0.01695   0.00746  -0.0332   1.0000   0.0480
  -3.750  -0.1210   0.01627   0.00670  -0.0326   1.0000   0.0540
  -3.500  -0.0963   0.01565   0.00609  -0.0321   1.0000   0.0644
  -3.250  -0.0711   0.01503   0.00558  -0.0317   1.0000   0.0851
  -3.000  -0.0385   0.01411   0.00514  -0.0331   0.9962   0.1827
  -2.500   0.0398   0.01139   0.00493  -0.0367   0.9819   1.0000
  -2.250   0.0832   0.01140   0.00466  -0.0399   0.9700   1.0000
  -2.000   0.1238   0.01137   0.00444  -0.0425   0.9552   1.0000
  -1.750   0.1601   0.01134   0.00424  -0.0441   0.9359   1.0000
  -1.500   0.1959   0.01131   0.00407  -0.0455   0.9143   1.0000
  -1.250   0.2284   0.01127   0.00391  -0.0461   0.8867   1.0000
  -1.000   0.2642   0.01122   0.00371  -0.0473   0.8606   1.0000
  -0.750   0.2973   0.01122   0.00354  -0.0478   0.8322   1.0000
  -0.500   0.3271   0.01128   0.00344  -0.0477   0.8018   1.0000
  -0.250   0.3547   0.01139   0.00339  -0.0472   0.7707   1.0000
   0.000   0.3817   0.01155   0.00339  -0.0466   0.7395   1.0000
   0.250   0.4082   0.01172   0.00343  -0.0461   0.7079   1.0000
   0.500   0.4345   0.01190   0.00348  -0.0455   0.6757   1.0000
   0.750   0.4606   0.01210   0.00355  -0.0449   0.6451   1.0000
   1.000   0.4866   0.01235   0.00362  -0.0443   0.6193   1.0000
   1.250   0.5127   0.01262   0.00374  -0.0438   0.5966   1.0000
   1.500   0.5389   0.01290   0.00393  -0.0433   0.5748   1.0000
   1.750   0.5650   0.01321   0.00416  -0.0429   0.5544   1.0000
   2.000   0.5912   0.01350   0.00440  -0.0426   0.5346   1.0000
   2.250   0.6174   0.01379   0.00466  -0.0422   0.5144   1.0000
   2.500   0.6434   0.01410   0.00492  -0.0418   0.4945   1.0000
   2.750   0.6695   0.01438   0.00524  -0.0415   0.4731   1.0000
   3.000   0.6953   0.01466   0.00552  -0.0411   0.4508   1.0000
   3.250   0.7210   0.01495   0.00581  -0.0408   0.4268   1.0000
   3.500   0.7464   0.01526   0.00611  -0.0403   0.4016   1.0000
   3.750   0.7715   0.01563   0.00646  -0.0399   0.3752   1.0000
   4.000   0.7962   0.01603   0.00682  -0.0395   0.3475   1.0000
   4.250   0.8208   0.01649   0.00723  -0.0390   0.3187   1.0000
   4.500   0.8451   0.01698   0.00768  -0.0386   0.2885   1.0000
   4.750   0.8691   0.01752   0.00821  -0.0382   0.2570   1.0000
   5.000   0.8925   0.01814   0.00877  -0.0377   0.2242   1.0000
   5.250   0.9156   0.01884   0.00940  -0.0373   0.1897   1.0000
   5.500   0.9380   0.01966   0.01012  -0.0368   0.1559   1.0000
   5.750   0.9595   0.02063   0.01100  -0.0362   0.1255   1.0000
   6.000   0.9807   0.02166   0.01199  -0.0355   0.1021   1.0000
   6.250   1.0009   0.02280   0.01307  -0.0348   0.0853   1.0000
   6.500   1.0205   0.02400   0.01430  -0.0339   0.0741   1.0000
   6.750   1.0406   0.02511   0.01556  -0.0331   0.0649   1.0000
   7.000   1.0591   0.02640   0.01693  -0.0321   0.0581   1.0000
   7.250   1.0775   0.02769   0.01834  -0.0310   0.0531   1.0000
   7.500   1.0939   0.02923   0.01994  -0.0299   0.0489   1.0000
   7.750   1.1122   0.03056   0.02149  -0.0288   0.0446   1.0000
   8.000   1.1287   0.03209   0.02313  -0.0277   0.0416   1.0000
   8.250   1.1428   0.03414   0.02522  -0.0264   0.0393   1.0000
   8.500   1.1593   0.03583   0.02726  -0.0252   0.0367   1.0000
   8.750   1.1737   0.03760   0.02929  -0.0240   0.0341   1.0000
   9.000   1.1865   0.03959   0.03146  -0.0227   0.0324   1.0000
   9.250   1.1974   0.04177   0.03379  -0.0214   0.0311   1.0000
   9.500   1.2050   0.04467   0.03682  -0.0200   0.0298   1.0000
   9.750   1.2087   0.04723   0.03983  -0.0181   0.0286   1.0000
  10.000   1.2071   0.04995   0.04291  -0.0160   0.0275   1.0000
  10.250   1.2011   0.05281   0.04608  -0.0138   0.0266   1.0000
  10.500   1.1921   0.05614   0.04970  -0.0124   0.0260   1.0000
  10.750   1.1802   0.06005   0.05388  -0.0119   0.0257   1.0000
  11.000   1.1656   0.06465   0.05874  -0.0126   0.0254   1.0000
  11.250   1.1483   0.07013   0.06448  -0.0148   0.0254   1.0000
  11.500   1.1281   0.07677   0.07137  -0.0184   0.0254   1.0000
  11.750   1.1039   0.08493   0.07977  -0.0237   0.0256   1.0000
  12.000   1.0740   0.09510   0.09015  -0.0306   0.0261   1.0000
  12.250   1.0375   0.10798   0.10318  -0.0391   0.0270   1.0000
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