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RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: RG 12A-1.8/9.0 AIRFOIL (rg12a189-il)
Reynolds number: 100,000
Max Cl/Cd: 50.76 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg12a189-il-100000.txt
Download as CSV file: xf-rg12a189-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3848   0.09295   0.08825  -0.0264   1.0000   0.1037
  -9.000  -0.4789   0.09751   0.09256  -0.0245   1.0000   0.0952
  -8.750  -0.4729   0.09438   0.08945  -0.0240   1.0000   0.0985
  -8.500  -0.4776   0.09103   0.08618  -0.0256   1.0000   0.1025
  -8.250  -0.5008   0.08769   0.08297  -0.0303   1.0000   0.1049
  -8.000  -0.5341   0.08411   0.07939  -0.0369   1.0000   0.1058
  -7.750  -0.5065   0.07973   0.07514  -0.0308   1.0000   0.1091
  -7.500  -0.5029   0.07684   0.07228  -0.0299   1.0000   0.1144
  -7.250  -0.5322   0.07317   0.06843  -0.0366   1.0000   0.1195
  -7.000  -0.4805   0.05844   0.05411  -0.0350   1.0000   0.1336
  -6.750  -0.4532   0.05497   0.05084  -0.0298   1.0000   0.1418
  -6.250  -0.4632   0.04739   0.04325  -0.0291   1.0000   0.1553
  -6.000  -0.4686   0.04340   0.03918  -0.0291   1.0000   0.1652
  -5.750  -0.4693   0.03998   0.03564  -0.0288   1.0000   0.1779
  -5.500  -0.4778   0.03980   0.03324  -0.0344   1.0000   0.0800
  -5.250  -0.4575   0.03448   0.02742  -0.0329   1.0000   0.0626
  -5.000  -0.4381   0.03064   0.02311  -0.0317   1.0000   0.0579
  -4.750  -0.4150   0.02727   0.01892  -0.0302   1.0000   0.0544
  -4.500  -0.3918   0.02499   0.01627  -0.0290   1.0000   0.0543
  -4.250  -0.3689   0.02307   0.01417  -0.0279   1.0000   0.0566
  -4.000  -0.3458   0.02188   0.01275  -0.0268   1.0000   0.0632
  -3.750  -0.3220   0.02011   0.01089  -0.0257   1.0000   0.0680
  -3.500  -0.2987   0.01895   0.00967  -0.0245   1.0000   0.0784
  -3.250  -0.2763   0.01751   0.00846  -0.0236   1.0000   0.1034
  -3.000  -0.2543   0.01582   0.00735  -0.0228   1.0000   0.1860
  -2.750  -0.2420   0.01316   0.00707  -0.0202   1.0000   0.5937
  -2.500  -0.2404   0.01319   0.00759  -0.0128   1.0000   0.8006
  -2.250  -0.2357   0.01331   0.00772  -0.0067   1.0000   0.8707
  -2.000  -0.2138   0.01345   0.00777  -0.0038   1.0000   0.9419
  -1.750  -0.0928   0.01387   0.00757  -0.0204   1.0000   1.0000
  -1.500  -0.0979   0.01372   0.00737  -0.0160   1.0000   1.0000
  -1.250  -0.0995   0.01364   0.00720  -0.0123   1.0000   1.0000
  -1.000  -0.0908   0.01369   0.00713  -0.0103   1.0000   1.0000
  -0.750  -0.0760   0.01386   0.00717  -0.0094   1.0000   1.0000
  -0.500  -0.0336   0.01432   0.00744  -0.0135   0.9925   1.0000
  -0.250   0.0183   0.01479   0.00776  -0.0190   0.9814   1.0000
   0.000   0.0706   0.01515   0.00801  -0.0245   0.9703   1.0000
   0.250   0.1194   0.01535   0.00811  -0.0291   0.9577   1.0000
   0.500   0.1674   0.01545   0.00816  -0.0334   0.9447   1.0000
   0.750   0.2148   0.01547   0.00815  -0.0374   0.9316   1.0000
   1.000   0.2623   0.01541   0.00808  -0.0413   0.9183   1.0000
   1.250   0.3106   0.01525   0.00794  -0.0451   0.9052   1.0000
   1.500   0.3608   0.01498   0.00773  -0.0490   0.8922   1.0000
   1.750   0.4078   0.01466   0.00746  -0.0521   0.8781   1.0000
   2.000   0.4528   0.01431   0.00716  -0.0547   0.8624   1.0000
   2.250   0.4958   0.01396   0.00689  -0.0568   0.8453   1.0000
   2.500   0.5261   0.01382   0.00677  -0.0566   0.8222   1.0000
   2.750   0.5581   0.01367   0.00664  -0.0566   0.7992   1.0000
   3.000   0.5882   0.01360   0.00654  -0.0562   0.7748   1.0000
   3.250   0.6137   0.01365   0.00661  -0.0551   0.7475   1.0000
   3.500   0.6387   0.01376   0.00668  -0.0539   0.7194   1.0000
   3.750   0.6631   0.01393   0.00679  -0.0526   0.6905   1.0000
   4.000   0.6866   0.01414   0.00695  -0.0512   0.6602   1.0000
   4.250   0.7091   0.01439   0.00720  -0.0497   0.6280   1.0000
   4.500   0.7316   0.01466   0.00742  -0.0483   0.5951   1.0000
   4.750   0.7541   0.01497   0.00763  -0.0468   0.5618   1.0000
   5.000   0.7753   0.01530   0.00794  -0.0452   0.5251   1.0000
   5.250   0.7964   0.01569   0.00828  -0.0437   0.4878   1.0000
   5.500   0.8168   0.01612   0.00861  -0.0420   0.4486   1.0000
   5.750   0.8362   0.01662   0.00902  -0.0403   0.4059   1.0000
   6.000   0.8549   0.01720   0.00951  -0.0386   0.3602   1.0000
   6.250   0.8725   0.01792   0.01008  -0.0368   0.3112   1.0000
   6.500   0.8882   0.01876   0.01074  -0.0348   0.2556   1.0000
   6.750   0.9024   0.01982   0.01147  -0.0329   0.1968   1.0000
   7.000   0.9157   0.02132   0.01264  -0.0309   0.1424   1.0000
   7.250   0.9272   0.02342   0.01438  -0.0285   0.1018   1.0000
   7.500   0.9434   0.02522   0.01613  -0.0267   0.0797   1.0000
   7.750   0.9632   0.02725   0.01815  -0.0253   0.0694   1.0000
   8.000   0.9871   0.03001   0.02074  -0.0249   0.0629   1.0000
   8.250   1.0110   0.03208   0.02322  -0.0238   0.0592   1.0000
   8.500   1.0314   0.03401   0.02534  -0.0228   0.0544   1.0000
   8.750   1.0533   0.03746   0.02888  -0.0224   0.0515   1.0000
   9.000   1.0695   0.04129   0.03312  -0.0210   0.0507   1.0000
   9.250   1.0804   0.04472   0.03708  -0.0188   0.0503   1.0000
   9.500   1.0870   0.04854   0.04139  -0.0166   0.0502   1.0000
   9.750   1.0880   0.05215   0.04549  -0.0140   0.0498   1.0000
  10.000   1.0839   0.05580   0.04959  -0.0113   0.0493   1.0000
  10.250   1.0753   0.05961   0.05378  -0.0087   0.0491   1.0000
  10.500   1.0611   0.06337   0.05785  -0.0061   0.0491   1.0000
  10.750   1.0442   0.06714   0.06184  -0.0036   0.0494   1.0000
  11.000   1.0247   0.07128   0.06616  -0.0023   0.0497   1.0000
  11.250   1.0080   0.07608   0.07109  -0.0023   0.0502   1.0000
  11.500   0.8349   0.08333   0.07913  -0.0069   0.0575   1.0000
  11.750   0.7965   0.09417   0.09005  -0.0137   0.0591   1.0000
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