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AG18 (ag18-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: AG18 (ag18-il)
Reynolds number: 1,000,000
Max Cl/Cd: 90.13 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag18-il-1000000-n5.txt
Download as CSV file: xf-ag18-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4546   0.11951   0.11796   0.0126   1.0000   0.0056
  -9.500  -0.5684   0.11605   0.11443   0.0237   1.0000   0.0056
  -8.000  -0.5568   0.08871   0.08717   0.0115   1.0000   0.0032
  -7.750  -0.5509   0.08509   0.08357   0.0092   1.0000   0.0031
  -7.500  -0.5439   0.08112   0.07960   0.0055   1.0000   0.0030
  -7.250  -0.5340   0.07534   0.07383  -0.0012   1.0000   0.0029
  -7.000  -0.5196   0.06880   0.06728  -0.0096   1.0000   0.0028
  -6.750  -0.5000   0.06087   0.05932  -0.0200   1.0000   0.0028
  -6.500  -0.4732   0.01848   0.01517  -0.0519   1.0000   0.0028
  -6.250  -0.4472   0.01607   0.01236  -0.0523   1.0000   0.0029
  -6.000  -0.4207   0.01491   0.01100  -0.0523   1.0000   0.0030
  -5.750  -0.3944   0.01250   0.00816  -0.0526   1.0000   0.0034
  -5.500  -0.3676   0.01181   0.00733  -0.0525   1.0000   0.0037
  -5.250  -0.3408   0.01127   0.00671  -0.0523   1.0000   0.0039
  -5.000  -0.3140   0.01069   0.00603  -0.0521   1.0000   0.0041
  -4.750  -0.2873   0.01010   0.00535  -0.0519   1.0000   0.0043
  -4.500  -0.2588   0.00950   0.00466  -0.0520   0.9986   0.0045
  -4.250  -0.2254   0.00902   0.00411  -0.0532   0.9924   0.0049
  -4.000  -0.1918   0.00863   0.00366  -0.0544   0.9829   0.0053
  -3.750  -0.1583   0.00816   0.00309  -0.0556   0.9693   0.0055
  -3.500  -0.1271   0.00776   0.00258  -0.0561   0.9479   0.0057
  -3.250  -0.0998   0.00737   0.00202  -0.0557   0.9197   0.0064
  -3.000  -0.0740   0.00718   0.00172  -0.0549   0.8889   0.0081
  -2.750  -0.0477   0.00711   0.00151  -0.0543   0.8584   0.0097
  -2.500  -0.0209   0.00700   0.00129  -0.0539   0.8279   0.0150
  -2.250   0.0061   0.00692   0.00114  -0.0536   0.7978   0.0251
  -2.000   0.0334   0.00683   0.00100  -0.0533   0.7688   0.0440
  -1.750   0.0609   0.00673   0.00089  -0.0532   0.7411   0.0714
  -1.500   0.0885   0.00664   0.00079  -0.0531   0.7138   0.1035
  -1.250   0.1162   0.00655   0.00072  -0.0530   0.6863   0.1421
  -1.000   0.1439   0.00647   0.00066  -0.0530   0.6583   0.1852
  -0.750   0.1716   0.00639   0.00062  -0.0529   0.6287   0.2387
  -0.500   0.1992   0.00634   0.00060  -0.0529   0.5975   0.2892
  -0.250   0.2269   0.00633   0.00058  -0.0529   0.5651   0.3360
   0.000   0.2546   0.00632   0.00059  -0.0529   0.5328   0.3872
   0.250   0.2822   0.00634   0.00062  -0.0528   0.4989   0.4351
   0.500   0.3098   0.00637   0.00065  -0.0528   0.4648   0.4851
   0.750   0.3373   0.00638   0.00070  -0.0528   0.4326   0.5425
   1.000   0.3647   0.00633   0.00076  -0.0527   0.4018   0.6235
   1.250   0.3908   0.00606   0.00084  -0.0524   0.3728   0.7803
   1.750   0.4430   0.00593   0.00095  -0.0513   0.3195   1.0000
   2.000   0.4707   0.00612   0.00102  -0.0513   0.2938   1.0000
   2.250   0.4983   0.00631   0.00111  -0.0512   0.2695   1.0000
   2.500   0.5260   0.00650   0.00120  -0.0511   0.2474   1.0000
   2.750   0.5535   0.00670   0.00131  -0.0511   0.2258   1.0000
   3.000   0.5810   0.00691   0.00144  -0.0510   0.2051   1.0000
   3.250   0.6085   0.00711   0.00157  -0.0509   0.1862   1.0000
   3.500   0.6359   0.00735   0.00172  -0.0508   0.1652   1.0000
   4.000   0.6905   0.00781   0.00205  -0.0506   0.1304   1.0000
   4.250   0.7178   0.00804   0.00224  -0.0505   0.1157   1.0000
   4.500   0.7449   0.00831   0.00244  -0.0504   0.1000   1.0000
   4.750   0.7719   0.00860   0.00266  -0.0502   0.0851   1.0000
   5.000   0.7989   0.00887   0.00289  -0.0501   0.0728   1.0000
   5.250   0.8257   0.00917   0.00316  -0.0499   0.0607   1.0000
   5.500   0.8526   0.00946   0.00342  -0.0498   0.0510   1.0000
   5.750   0.8793   0.00977   0.00371  -0.0496   0.0417   1.0000
   6.000   0.9058   0.01012   0.00403  -0.0494   0.0328   1.0000
   6.250   0.9321   0.01051   0.00438  -0.0492   0.0240   1.0000
   6.500   0.9583   0.01092   0.00476  -0.0490   0.0175   1.0000
   6.750   0.9846   0.01127   0.00515  -0.0488   0.0138   1.0000
   7.000   1.0105   0.01172   0.00559  -0.0485   0.0099   1.0000
   7.250   1.0365   0.01211   0.00602  -0.0483   0.0077   1.0000
   7.500   1.0619   0.01265   0.00656  -0.0480   0.0052   1.0000
   7.750   1.0876   0.01308   0.00704  -0.0477   0.0043   1.0000
   8.000   1.1128   0.01360   0.00760  -0.0474   0.0034   1.0000
   8.250   1.1375   0.01429   0.00837  -0.0469   0.0027   1.0000
   8.500   1.1625   0.01481   0.00899  -0.0466   0.0025   1.0000
   8.750   1.1871   0.01539   0.00966  -0.0462   0.0024   1.0000
   9.000   1.2115   0.01601   0.01038  -0.0458   0.0022   1.0000
   9.250   1.2354   0.01668   0.01114  -0.0453   0.0020   1.0000
   9.500   1.2590   0.01739   0.01194  -0.0449   0.0018   1.0000
   9.750   1.2821   0.01815   0.01280  -0.0444   0.0017   1.0000
  10.000   1.3044   0.01904   0.01379  -0.0438   0.0015   1.0000
  10.250   1.3244   0.02036   0.01528  -0.0430   0.0013   1.0000
  10.500   1.3423   0.02200   0.01715  -0.0420   0.0012   1.0000
  10.750   1.3623   0.02309   0.01841  -0.0412   0.0012   1.0000
  11.000   1.3811   0.02433   0.01980  -0.0404   0.0011   1.0000
  11.250   1.3983   0.02574   0.02139  -0.0394   0.0011   1.0000
  11.500   1.4135   0.02734   0.02318  -0.0383   0.0011   1.0000
  11.750   1.4264   0.02914   0.02519  -0.0371   0.0010   1.0000
  12.000   1.4363   0.03119   0.02745  -0.0357   0.0010   1.0000
  12.250   1.4424   0.03348   0.02997  -0.0342   0.0010   1.0000
  12.500   1.4437   0.03602   0.03274  -0.0325   0.0010   1.0000
  12.750   1.4358   0.03871   0.03563  -0.0300   0.0010   1.0000
  13.000   1.4235   0.04217   0.03928  -0.0291   0.0010   1.0000
  13.250   1.4085   0.04713   0.04444  -0.0309   0.0010   1.0000
  13.500   1.3910   0.05415   0.05167  -0.0359   0.0010   1.0000
  13.750   1.3695   0.06377   0.06150  -0.0436   0.0010   1.0000
  14.000   1.3406   0.07567   0.07357  -0.0518   0.0010   1.0000
  14.250   1.3068   0.08784   0.08587  -0.0587   0.0010   1.0000
  14.500   1.2708   0.09985   0.09797  -0.0647   0.0010   1.0000
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