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AG18 (ag18-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: AG18 (ag18-il)
Reynolds number: 200,000
Max Cl/Cd: 65.13 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ag18-il-200000.txt
Download as CSV file: xf-ag18-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.5240   0.09492   0.09154   0.0095   1.0000   0.0315
  -7.500  -0.5188   0.09136   0.08802   0.0074   1.0000   0.0326
  -7.250  -0.5133   0.08768   0.08438   0.0045   1.0000   0.0337
  -7.000  -0.5035   0.08345   0.08017  -0.0003   1.0000   0.0352
  -6.750  -0.4854   0.07821   0.07495  -0.0103   1.0000   0.0373
  -6.500  -0.4560   0.07188   0.06852  -0.0242   1.0000   0.0383
  -6.250  -0.4331   0.06600   0.06248  -0.0317   1.0000   0.0385
  -6.000  -0.4302   0.05971   0.05630  -0.0318   1.0000   0.0400
  -5.750  -0.4160   0.05695   0.05356  -0.0317   1.0000   0.0419
  -5.500  -0.3944   0.05284   0.04937  -0.0352   1.0000   0.0448
  -5.250  -0.3544   0.04523   0.04101  -0.0460   1.0000   0.0517
  -5.000  -0.3433   0.04293   0.03909  -0.0441   1.0000   0.0563
  -4.750  -0.3123   0.03762   0.03321  -0.0488   1.0000   0.0660
  -4.500  -0.2906   0.03492   0.03054  -0.0490   1.0000   0.0693
  -4.000  -0.2229   0.02219   0.01619  -0.0514   1.0000   0.0345
  -3.750  -0.1930   0.01838   0.01166  -0.0512   1.0000   0.0300
  -3.500  -0.1651   0.01625   0.00914  -0.0506   1.0000   0.0293
  -3.250  -0.1381   0.01471   0.00742  -0.0501   1.0000   0.0308
  -3.000  -0.1114   0.01373   0.00635  -0.0496   1.0000   0.0357
  -2.750  -0.0846   0.01244   0.00500  -0.0492   1.0000   0.0424
  -2.500  -0.0573   0.01144   0.00399  -0.0489   1.0000   0.0567
  -2.250  -0.0294   0.01038   0.00321  -0.0490   1.0000   0.1203
  -2.000  -0.0021   0.00938   0.00293  -0.0495   1.0000   0.2872
  -1.750   0.0242   0.00877   0.00285  -0.0495   1.0000   0.4410
  -1.500   0.0496   0.00818   0.00280  -0.0490   1.0000   0.5931
  -1.250   0.0684   0.00712   0.00267  -0.0461   1.0000   1.0000
  -1.000   0.0952   0.00719   0.00257  -0.0460   1.0000   1.0000
  -0.750   0.1219   0.00728   0.00253  -0.0460   1.0000   1.0000
  -0.500   0.1483   0.00740   0.00255  -0.0460   1.0000   1.0000
  -0.250   0.1829   0.00752   0.00256  -0.0478   0.9955   1.0000
   0.000   0.2314   0.00755   0.00252  -0.0521   0.9828   1.0000
   0.250   0.2774   0.00754   0.00245  -0.0557   0.9687   1.0000
   0.500   0.3170   0.00752   0.00240  -0.0578   0.9485   1.0000
   0.750   0.3535   0.00750   0.00233  -0.0591   0.9263   1.0000
   1.000   0.3835   0.00750   0.00228  -0.0589   0.8990   1.0000
   1.250   0.4095   0.00756   0.00225  -0.0578   0.8682   1.0000
   1.500   0.4343   0.00765   0.00225  -0.0564   0.8356   1.0000
   1.750   0.4589   0.00779   0.00228  -0.0551   0.8010   1.0000
   2.000   0.4836   0.00796   0.00231  -0.0539   0.7643   1.0000
   2.250   0.5086   0.00817   0.00237  -0.0528   0.7250   1.0000
   2.500   0.5337   0.00841   0.00245  -0.0518   0.6832   1.0000
   2.750   0.5590   0.00868   0.00255  -0.0509   0.6377   1.0000
   3.000   0.5843   0.00900   0.00271  -0.0501   0.5888   1.0000
   3.250   0.6096   0.00936   0.00287  -0.0494   0.5378   1.0000
   3.500   0.6349   0.00977   0.00307  -0.0488   0.4860   1.0000
   3.750   0.6603   0.01022   0.00331  -0.0483   0.4364   1.0000
   4.000   0.6859   0.01068   0.00360  -0.0479   0.3897   1.0000
   4.250   0.7115   0.01116   0.00396  -0.0475   0.3462   1.0000
   4.500   0.7371   0.01166   0.00432  -0.0471   0.3063   1.0000
   4.750   0.7626   0.01219   0.00472  -0.0468   0.2683   1.0000
   5.000   0.7881   0.01273   0.00516  -0.0465   0.2330   1.0000
   5.250   0.8135   0.01332   0.00564  -0.0462   0.1991   1.0000
   5.500   0.8388   0.01396   0.00624  -0.0459   0.1682   1.0000
   5.750   0.8637   0.01467   0.00687  -0.0455   0.1405   1.0000
   6.000   0.8885   0.01544   0.00759  -0.0451   0.1161   1.0000
   6.250   0.9124   0.01641   0.00847  -0.0446   0.0957   1.0000
   6.500   0.9370   0.01722   0.00934  -0.0441   0.0772   1.0000
   6.750   0.9607   0.01827   0.01041  -0.0435   0.0620   1.0000
   7.000   0.9837   0.01948   0.01171  -0.0428   0.0492   1.0000
   7.250   1.0065   0.02081   0.01313  -0.0420   0.0389   1.0000
   7.500   1.0272   0.02291   0.01537  -0.0409   0.0323   1.0000
   7.750   1.0494   0.02432   0.01689  -0.0401   0.0268   1.0000
   8.000   1.0684   0.02712   0.01998  -0.0389   0.0231   1.0000
   8.250   1.0885   0.02970   0.02293  -0.0377   0.0212   1.0000
   8.500   1.1060   0.03281   0.02648  -0.0363   0.0200   1.0000
   8.750   1.1199   0.03657   0.03073  -0.0349   0.0194   1.0000
   9.000   1.1279   0.04132   0.03606  -0.0333   0.0194   1.0000
   9.250   1.1273   0.04709   0.04246  -0.0317   0.0198   1.0000
   9.500   1.1200   0.05296   0.04883  -0.0306   0.0201   1.0000
   9.750   1.1058   0.05879   0.05506  -0.0301   0.0206   1.0000
  10.000   1.0857   0.06391   0.06045  -0.0300   0.0210   1.0000
  10.250   1.0636   0.06976   0.06649  -0.0329   0.0213   1.0000
  10.500   1.0427   0.07752   0.07442  -0.0398   0.0216   1.0000
  10.750   1.0213   0.08833   0.08534  -0.0498   0.0219   1.0000
  11.000   0.9979   0.10122   0.09825  -0.0590   0.0225   1.0000
  11.250   0.9791   0.11176   0.10875  -0.0645   0.0232   1.0000
  11.500   0.9654   0.12008   0.11703  -0.0684   0.0239   1.0000
  11.750   0.9396   0.13666   0.13352  -0.0765   0.0306   1.0000
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