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RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: RG 12A-1.8/9.0 AIRFOIL (rg12a189-il)
Reynolds number: 1,000,000
Max Cl/Cd: 83.52 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg12a189-il-1000000-n5.txt
Download as CSV file: xf-rg12a189-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 12A-1.8/9.0 AIRFOIL                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5252   0.08882   0.08718  -0.0240   1.0000   0.0029
  -9.750  -0.5353   0.08290   0.08128  -0.0267   1.0000   0.0027
  -8.750  -0.7118   0.02602   0.02300  -0.0466   0.9957   0.0029
  -8.500  -0.6888   0.02241   0.01894  -0.0481   0.9938   0.0030
  -8.250  -0.6648   0.02027   0.01649  -0.0486   0.9914   0.0031
  -8.000  -0.6388   0.01846   0.01441  -0.0492   0.9892   0.0032
  -7.750  -0.6109   0.01698   0.01269  -0.0500   0.9873   0.0033
  -7.500  -0.5816   0.01573   0.01124  -0.0509   0.9857   0.0034
  -7.250  -0.5514   0.01448   0.00977  -0.0519   0.9844   0.0034
  -7.000  -0.5199   0.01361   0.00877  -0.0530   0.9833   0.0035
  -6.750  -0.4959   0.01302   0.00809  -0.0524   0.9792   0.0036
  -6.500  -0.4669   0.01252   0.00751  -0.0529   0.9763   0.0038
  -6.250  -0.4369   0.01175   0.00663  -0.0536   0.9738   0.0039
  -6.000  -0.4061   0.01083   0.00559  -0.0545   0.9718   0.0041
  -5.750  -0.3779   0.01023   0.00490  -0.0547   0.9682   0.0044
  -5.500  -0.3511   0.00977   0.00439  -0.0546   0.9629   0.0047
  -5.250  -0.3194   0.00937   0.00396  -0.0555   0.9594   0.0050
  -5.000  -0.2885   0.00902   0.00357  -0.0562   0.9549   0.0056
  -4.750  -0.2577   0.00870   0.00321  -0.0569   0.9484   0.0061
  -4.500  -0.2240   0.00837   0.00283  -0.0582   0.9423   0.0068
  -4.250  -0.1915   0.00807   0.00250  -0.0592   0.9330   0.0083
  -4.000  -0.1593   0.00784   0.00223  -0.0602   0.9210   0.0106
  -3.750  -0.1290   0.00762   0.00197  -0.0607   0.9058   0.0149
  -3.500  -0.1008   0.00740   0.00174  -0.0608   0.8882   0.0282
  -3.250  -0.0737   0.00725   0.00158  -0.0606   0.8682   0.0427
  -3.000  -0.0475   0.00710   0.00143  -0.0602   0.8468   0.0628
  -2.750  -0.0217   0.00694   0.00130  -0.0598   0.8242   0.0954
  -2.500   0.0038   0.00680   0.00117  -0.0594   0.8005   0.1307
  -2.250   0.0293   0.00668   0.00108  -0.0590   0.7763   0.1677
  -2.000   0.0547   0.00650   0.00099  -0.0586   0.7523   0.2253
  -1.750   0.0803   0.00635   0.00092  -0.0582   0.7290   0.2807
  -1.500   0.1061   0.00624   0.00085  -0.0579   0.7062   0.3290
  -1.250   0.1320   0.00608   0.00080  -0.0576   0.6845   0.3930
  -1.000   0.1574   0.00580   0.00075  -0.0573   0.6636   0.4961
  -0.750   0.1824   0.00546   0.00073  -0.0569   0.6429   0.6189
  -0.500   0.2083   0.00538   0.00076  -0.0566   0.6222   0.6874
  -0.250   0.2350   0.00543   0.00079  -0.0563   0.6020   0.7172
   0.000   0.2619   0.00550   0.00082  -0.0560   0.5814   0.7350
   0.250   0.2888   0.00558   0.00086  -0.0558   0.5614   0.7487
   0.500   0.3158   0.00568   0.00089  -0.0556   0.5407   0.7603
   0.750   0.3426   0.00578   0.00094  -0.0554   0.5191   0.7703
   1.000   0.3694   0.00589   0.00099  -0.0551   0.4970   0.7799
   1.250   0.3963   0.00602   0.00105  -0.0549   0.4753   0.7892
   1.500   0.4229   0.00614   0.00112  -0.0547   0.4532   0.7997
   1.750   0.4494   0.00626   0.00120  -0.0544   0.4311   0.8106
   2.000   0.4759   0.00642   0.00128  -0.0541   0.4073   0.8191
   2.250   0.5024   0.00657   0.00138  -0.0539   0.3833   0.8249
   2.500   0.5290   0.00676   0.00147  -0.0537   0.3574   0.8294
   2.750   0.5555   0.00693   0.00157  -0.0534   0.3350   0.8333
   3.000   0.5818   0.00712   0.00170  -0.0532   0.3102   0.8378
   3.250   0.6080   0.00734   0.00183  -0.0529   0.2837   0.8425
   3.500   0.6337   0.00760   0.00198  -0.0526   0.2541   0.8469
   3.750   0.6590   0.00789   0.00215  -0.0522   0.2200   0.8521
   4.000   0.6830   0.00834   0.00239  -0.0517   0.1711   0.8580
   4.250   0.7079   0.00866   0.00261  -0.0512   0.1414   0.8636
   4.500   0.7333   0.00894   0.00281  -0.0508   0.1196   0.8699
   4.750   0.7584   0.00923   0.00304  -0.0504   0.0997   0.8763
   5.000   0.7830   0.00954   0.00329  -0.0499   0.0795   0.8838
   5.250   0.8071   0.00988   0.00358  -0.0493   0.0587   0.8924
   5.500   0.8311   0.01021   0.00386  -0.0486   0.0434   0.9026
   5.750   0.8544   0.01054   0.00416  -0.0478   0.0300   0.9151
   6.000   0.8765   0.01089   0.00450  -0.0467   0.0184   0.9311
   6.250   0.8995   0.01115   0.00480  -0.0458   0.0141   0.9554
   6.500   0.9299   0.01147   0.00515  -0.0466   0.0124   1.0000
   6.750   0.9549   0.01182   0.00553  -0.0462   0.0112   1.0000
   7.000   0.9796   0.01222   0.00597  -0.0457   0.0104   1.0000
   7.250   1.0038   0.01265   0.00645  -0.0452   0.0098   1.0000
   7.500   1.0284   0.01302   0.00687  -0.0447   0.0097   1.0000
   7.750   1.0526   0.01342   0.00734  -0.0442   0.0095   1.0000
   8.000   1.0767   0.01380   0.00777  -0.0438   0.0091   1.0000
   8.250   1.1004   0.01422   0.00824  -0.0432   0.0087   1.0000
   8.500   1.1241   0.01463   0.00869  -0.0427   0.0082   1.0000
   8.750   1.1473   0.01507   0.00916  -0.0421   0.0077   1.0000
   9.000   1.1699   0.01556   0.00969  -0.0414   0.0073   1.0000
   9.250   1.1914   0.01616   0.01036  -0.0406   0.0068   1.0000
   9.500   1.2097   0.01706   0.01137  -0.0392   0.0063   1.0000
   9.750   1.2320   0.01750   0.01186  -0.0385   0.0061   1.0000
  10.000   1.2542   0.01792   0.01234  -0.0379   0.0059   1.0000
  10.250   1.2759   0.01838   0.01284  -0.0371   0.0055   1.0000
  10.500   1.2970   0.01886   0.01338  -0.0363   0.0052   1.0000
  10.750   1.3175   0.01937   0.01394  -0.0354   0.0048   1.0000
  11.000   1.3370   0.01994   0.01456  -0.0344   0.0045   1.0000
  11.250   1.3563   0.02050   0.01516  -0.0333   0.0042   1.0000
  11.500   1.3727   0.02126   0.01599  -0.0319   0.0038   1.0000
  11.750   1.3889   0.02199   0.01679  -0.0304   0.0036   1.0000
  12.000   1.4034   0.02271   0.01761  -0.0287   0.0034   1.0000
  12.250   1.4154   0.02344   0.01842  -0.0265   0.0033   1.0000
  12.500   1.4258   0.02424   0.01930  -0.0242   0.0031   1.0000
  12.750   1.4362   0.02505   0.02018  -0.0220   0.0028   1.0000
  13.000   1.4451   0.02597   0.02118  -0.0198   0.0027   1.0000
  13.250   1.4533   0.02696   0.02224  -0.0176   0.0025   1.0000
  13.500   1.4585   0.02819   0.02356  -0.0153   0.0024   1.0000
  13.750   1.4616   0.02964   0.02512  -0.0131   0.0022   1.0000
  14.000   1.4619   0.03138   0.02698  -0.0110   0.0021   1.0000
  14.250   1.4620   0.03326   0.02899  -0.0093   0.0020   1.0000
  14.500   1.4628   0.03522   0.03107  -0.0080   0.0020   1.0000
  14.750   1.4592   0.03777   0.03375  -0.0070   0.0019   1.0000
  15.000   1.4567   0.04044   0.03654  -0.0066   0.0019   1.0000
  15.250   1.4514   0.04366   0.03990  -0.0066   0.0018   1.0000
  15.500   1.4447   0.04733   0.04371  -0.0073   0.0018   1.0000
  15.750   1.4365   0.05151   0.04803  -0.0085   0.0018   1.0000
  16.000   1.4237   0.05669   0.05337  -0.0106   0.0018   1.0000
  16.250   1.4093   0.06254   0.05936  -0.0133   0.0017   1.0000
  16.500   1.3957   0.06859   0.06555  -0.0164   0.0017   1.0000
  16.750   1.3744   0.07636   0.07349  -0.0207   0.0017   1.0000
  17.000   1.3557   0.08408   0.08134  -0.0250   0.0017   1.0000
  17.250   1.3208   0.09543   0.09289  -0.0316   0.0017   1.0000
  17.500   1.2889   0.10667   0.10429  -0.0381   0.0018   1.0000
  17.750   1.2568   0.11842   0.11619  -0.0449   0.0018   1.0000
  18.000   1.2202   0.13160   0.12953  -0.0527   0.0019   1.0000
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