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AG18 (ag18-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: AG18 (ag18-il)
Reynolds number: 100,000
Max Cl/Cd: 48.53 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag18-il-100000-n5.txt
Download as CSV file: xf-ag18-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5526   0.11917   0.11420   0.0153   1.0000   0.0376
  -9.000  -0.5498   0.11588   0.11095   0.0120   1.0000   0.0379
  -8.750  -0.5461   0.11238   0.10749   0.0090   1.0000   0.0381
  -7.750  -0.5215   0.09637   0.09162   0.0072   1.0000   0.0427
  -7.500  -0.5161   0.09292   0.08821   0.0053   1.0000   0.0445
  -7.250  -0.5104   0.08920   0.08454   0.0024   1.0000   0.0457
  -7.000  -0.5014   0.08497   0.08035  -0.0017   1.0000   0.0463
  -6.750  -0.4903   0.08037   0.07578  -0.0064   1.0000   0.0457
  -6.250  -0.4536   0.06525   0.06053  -0.0235   1.0000   0.0250
  -6.000  -0.4352   0.05978   0.05499  -0.0286   1.0000   0.0240
  -5.750  -0.4132   0.05370   0.04878  -0.0343   1.0000   0.0231
  -5.500  -0.3885   0.04731   0.04214  -0.0397   1.0000   0.0222
  -5.250  -0.3619   0.04100   0.03547  -0.0442   1.0000   0.0215
  -5.000  -0.3343   0.03533   0.02929  -0.0474   1.0000   0.0209
  -4.750  -0.3061   0.03055   0.02390  -0.0494   1.0000   0.0207
  -4.500  -0.2778   0.02678   0.01951  -0.0504   1.0000   0.0208
  -4.250  -0.2497   0.02384   0.01601  -0.0507   1.0000   0.0213
  -4.000  -0.2221   0.02173   0.01341  -0.0506   1.0000   0.0233
  -3.750  -0.1946   0.02035   0.01160  -0.0503   1.0000   0.0264
  -3.500  -0.1681   0.01822   0.00931  -0.0500   1.0000   0.0287
  -3.250  -0.1416   0.01693   0.00791  -0.0496   1.0000   0.0320
  -3.000  -0.1151   0.01597   0.00680  -0.0492   1.0000   0.0389
  -2.750  -0.0886   0.01499   0.00577  -0.0489   1.0000   0.0505
  -2.500  -0.0620   0.01410   0.00493  -0.0487   1.0000   0.0781
  -2.250  -0.0355   0.01320   0.00435  -0.0487   1.0000   0.1425
  -2.000  -0.0096   0.01245   0.00404  -0.0487   1.0000   0.2529
  -1.750   0.0158   0.01187   0.00387  -0.0484   1.0000   0.3798
  -1.500   0.0415   0.01136   0.00375  -0.0480   1.0000   0.5055
  -1.250   0.0647   0.01075   0.00360  -0.0468   1.0000   0.6539
  -1.000   0.0846   0.00998   0.00341  -0.0443   1.0000   1.0000
  -0.750   0.1106   0.01007   0.00331  -0.0442   1.0000   1.0000
  -0.500   0.1434   0.01017   0.00325  -0.0454   0.9945   1.0000
  -0.250   0.1866   0.01025   0.00315  -0.0487   0.9783   1.0000
   0.000   0.2275   0.01031   0.00309  -0.0513   0.9594   1.0000
   0.250   0.2668   0.01036   0.00305  -0.0535   0.9386   1.0000
   0.500   0.3038   0.01041   0.00301  -0.0550   0.9150   1.0000
   0.750   0.3376   0.01046   0.00299  -0.0558   0.8882   1.0000
   1.000   0.3686   0.01053   0.00297  -0.0559   0.8588   1.0000
   1.250   0.3968   0.01063   0.00298  -0.0553   0.8265   1.0000
   1.500   0.4238   0.01075   0.00300  -0.0545   0.7927   1.0000
   1.750   0.4498   0.01091   0.00308  -0.0535   0.7570   1.0000
   2.000   0.4756   0.01111   0.00314  -0.0525   0.7196   1.0000
   2.250   0.5014   0.01133   0.00323  -0.0516   0.6799   1.0000
   2.500   0.5269   0.01159   0.00335  -0.0507   0.6376   1.0000
   2.750   0.5523   0.01189   0.00350  -0.0498   0.5932   1.0000
   3.000   0.5776   0.01224   0.00373  -0.0490   0.5474   1.0000
   3.250   0.6029   0.01263   0.00395  -0.0483   0.5015   1.0000
   3.500   0.6282   0.01305   0.00421  -0.0476   0.4561   1.0000
   3.750   0.6535   0.01351   0.00452  -0.0471   0.4127   1.0000
   4.000   0.6788   0.01400   0.00487  -0.0465   0.3716   1.0000
   4.250   0.7041   0.01451   0.00533  -0.0461   0.3331   1.0000
   4.500   0.7293   0.01505   0.00577  -0.0457   0.2975   1.0000
   4.750   0.7546   0.01560   0.00626  -0.0453   0.2631   1.0000
   5.000   0.7797   0.01619   0.00680  -0.0449   0.2315   1.0000
   5.250   0.8048   0.01683   0.00739  -0.0445   0.2019   1.0000
   5.500   0.8296   0.01750   0.00809  -0.0441   0.1737   1.0000
   5.750   0.8542   0.01825   0.00881  -0.0437   0.1492   1.0000
   6.000   0.8787   0.01902   0.00962  -0.0433   0.1253   1.0000
   6.250   0.9027   0.01991   0.01053  -0.0428   0.1063   1.0000
   6.500   0.9265   0.02084   0.01151  -0.0423   0.0874   1.0000
   6.750   0.9496   0.02194   0.01266  -0.0418   0.0729   1.0000
   7.000   0.9721   0.02313   0.01397  -0.0412   0.0592   1.0000
   7.250   0.9944   0.02444   0.01544  -0.0405   0.0486   1.0000
   7.500   1.0159   0.02590   0.01707  -0.0397   0.0394   1.0000
   7.750   1.0357   0.02774   0.01905  -0.0388   0.0333   1.0000
   8.000   1.0560   0.02956   0.02114  -0.0378   0.0282   1.0000
   8.250   1.0735   0.03166   0.02338  -0.0370   0.0238   1.0000
   8.500   1.0915   0.03428   0.02643  -0.0358   0.0216   1.0000
   8.750   1.1071   0.03731   0.02988  -0.0345   0.0198   1.0000
   9.000   1.1211   0.03998   0.03289  -0.0335   0.0180   1.0000
   9.250   1.1316   0.04260   0.03571  -0.0327   0.0163   1.0000
   9.500   1.1352   0.04673   0.04028  -0.0316   0.0153   1.0000
   9.750   1.1364   0.05075   0.04490  -0.0306   0.0146   1.0000
  10.000   1.1300   0.05532   0.04991  -0.0298   0.0144   1.0000
  10.250   1.1166   0.05985   0.05477  -0.0293   0.0143   1.0000
  10.500   1.0994   0.06479   0.05997  -0.0305   0.0144   1.0000
  10.750   1.0813   0.07101   0.06640  -0.0346   0.0145   1.0000
  11.000   1.0631   0.07885   0.07433  -0.0411   0.0147   1.0000
  11.250   1.0444   0.08819   0.08378  -0.0486   0.0150   1.0000
  11.500   1.0258   0.09790   0.09354  -0.0553   0.0154   1.0000
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