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RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: RG 12A-1.8/9.0 AIRFOIL (rg12a189-il)
Reynolds number: 500,000
Max Cl/Cd: 74.69 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg12a189-il-500000-n5.txt
Download as CSV file: xf-rg12a189-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5100   0.08506   0.08278  -0.0266   1.0000   0.0049
  -9.250  -0.5184   0.07968   0.07743  -0.0290   1.0000   0.0048
  -9.000  -0.5302   0.07397   0.07177  -0.0320   1.0000   0.0047
  -8.750  -0.5478   0.06801   0.06587  -0.0362   1.0000   0.0048
  -8.500  -0.5752   0.06112   0.05895  -0.0395   1.0000   0.0046
  -8.250  -0.5927   0.05438   0.05209  -0.0407   1.0000   0.0045
  -8.000  -0.6095   0.04684   0.04434  -0.0401   1.0000   0.0045
  -7.750  -0.6301   0.03594   0.03291  -0.0383   0.9997   0.0046
  -7.500  -0.6155   0.02703   0.02314  -0.0407   0.9960   0.0047
  -7.250  -0.5907   0.02316   0.01872  -0.0419   0.9936   0.0048
  -7.000  -0.5630   0.02159   0.01688  -0.0428   0.9910   0.0052
  -6.750  -0.5343   0.01982   0.01480  -0.0436   0.9884   0.0056
  -6.500  -0.5044   0.01803   0.01268  -0.0446   0.9861   0.0058
  -6.250  -0.4734   0.01645   0.01083  -0.0456   0.9842   0.0059
  -6.000  -0.4444   0.01524   0.00944  -0.0461   0.9814   0.0060
  -5.750  -0.4164   0.01423   0.00825  -0.0463   0.9776   0.0061
  -5.500  -0.3857   0.01338   0.00728  -0.0471   0.9744   0.0064
  -5.250  -0.3541   0.01235   0.00614  -0.0482   0.9719   0.0068
  -5.000  -0.3247   0.01173   0.00547  -0.0487   0.9679   0.0075
  -4.750  -0.2958   0.01123   0.00492  -0.0490   0.9629   0.0082
  -4.500  -0.2634   0.01078   0.00439  -0.0500   0.9595   0.0093
  -4.250  -0.2325   0.01032   0.00388  -0.0508   0.9553   0.0114
  -4.000  -0.2035   0.00993   0.00346  -0.0510   0.9488   0.0140
  -3.750  -0.1690   0.00952   0.00304  -0.0524   0.9447   0.0202
  -3.500  -0.1387   0.00913   0.00272  -0.0530   0.9372   0.0401
  -3.250  -0.1043   0.00873   0.00245  -0.0546   0.9310   0.0707
  -3.000  -0.0722   0.00839   0.00222  -0.0556   0.9217   0.1060
  -2.750  -0.0390   0.00798   0.00199  -0.0570   0.9115   0.1620
  -2.500  -0.0072   0.00754   0.00178  -0.0581   0.8988   0.2375
  -2.250   0.0231   0.00717   0.00160  -0.0587   0.8829   0.3119
  -2.000   0.0519   0.00686   0.00145  -0.0591   0.8646   0.3850
  -1.750   0.0790   0.00653   0.00131  -0.0590   0.8445   0.4722
  -1.500   0.1029   0.00599   0.00125  -0.0583   0.8225   0.6290
  -1.250   0.1280   0.00591   0.00129  -0.0575   0.8000   0.7074
  -1.000   0.1542   0.00596   0.00128  -0.0570   0.7765   0.7341
  -0.750   0.1802   0.00603   0.00128  -0.0564   0.7531   0.7537
  -0.500   0.2062   0.00612   0.00128  -0.0558   0.7298   0.7692
  -0.250   0.2321   0.00622   0.00129  -0.0553   0.7067   0.7821
   0.000   0.2580   0.00632   0.00131  -0.0547   0.6844   0.7934
   0.250   0.2839   0.00643   0.00133  -0.0542   0.6625   0.8044
   0.500   0.3099   0.00653   0.00137  -0.0537   0.6408   0.8152
   1.000   0.3609   0.00674   0.00147  -0.0525   0.5978   0.8374
   1.250   0.3865   0.00686   0.00153  -0.0519   0.5762   0.8473
   1.500   0.4123   0.00698   0.00159  -0.0514   0.5531   0.8543
   1.750   0.4385   0.00712   0.00165  -0.0511   0.5304   0.8599
   2.000   0.4641   0.00726   0.00172  -0.0506   0.5069   0.8646
   2.250   0.4901   0.00741   0.00181  -0.0503   0.4834   0.8699
   2.500   0.5159   0.00757   0.00190  -0.0498   0.4585   0.8752
   2.750   0.5412   0.00775   0.00200  -0.0493   0.4334   0.8808
   3.000   0.5667   0.00795   0.00212  -0.0489   0.4063   0.8869
   3.250   0.5915   0.00814   0.00226  -0.0483   0.3800   0.8934
   3.500   0.6167   0.00835   0.00241  -0.0478   0.3543   0.9010
   3.750   0.6408   0.00858   0.00256  -0.0471   0.3257   0.9089
   4.750   0.7379   0.00991   0.00343  -0.0448   0.1837   0.9613
   5.000   0.7685   0.01035   0.00372  -0.0457   0.1470   0.9855
   5.250   0.7944   0.01081   0.00405  -0.0457   0.1171   1.0000
   5.500   0.8183   0.01130   0.00440  -0.0453   0.0889   1.0000
   5.750   0.8427   0.01174   0.00475  -0.0449   0.0688   1.0000
   6.000   0.8668   0.01220   0.00514  -0.0444   0.0520   1.0000
   6.250   0.8907   0.01268   0.00556  -0.0439   0.0362   1.0000
   6.500   0.9138   0.01324   0.00607  -0.0433   0.0227   1.0000
   6.750   0.9377   0.01372   0.00655  -0.0427   0.0181   1.0000
   7.000   0.9610   0.01425   0.00712  -0.0420   0.0153   1.0000
   7.250   0.9848   0.01471   0.00764  -0.0415   0.0143   1.0000
   7.500   1.0082   0.01521   0.00822  -0.0408   0.0136   1.0000
   7.750   1.0310   0.01576   0.00887  -0.0401   0.0130   1.0000
   8.000   1.0532   0.01635   0.00954  -0.0393   0.0124   1.0000
   8.250   1.0747   0.01700   0.01027  -0.0384   0.0118   1.0000
   8.500   1.0954   0.01770   0.01104  -0.0375   0.0112   1.0000
   8.750   1.1133   0.01868   0.01212  -0.0361   0.0103   1.0000
   9.000   1.1298   0.01978   0.01334  -0.0345   0.0098   1.0000
   9.250   1.1500   0.02044   0.01410  -0.0335   0.0095   1.0000
   9.500   1.1699   0.02110   0.01487  -0.0325   0.0090   1.0000
   9.750   1.1885   0.02184   0.01572  -0.0314   0.0084   1.0000
  10.000   1.2060   0.02265   0.01662  -0.0301   0.0079   1.0000
  10.250   1.2222   0.02354   0.01761  -0.0286   0.0075   1.0000
  10.500   1.2372   0.02445   0.01861  -0.0271   0.0071   1.0000
  10.750   1.2496   0.02544   0.01969  -0.0252   0.0067   1.0000
  11.000   1.2530   0.02696   0.02134  -0.0220   0.0064   1.0000
  11.250   1.2594   0.02825   0.02276  -0.0194   0.0061   1.0000
  11.500   1.2681   0.02935   0.02400  -0.0172   0.0059   1.0000
  11.750   1.2788   0.03026   0.02504  -0.0154   0.0055   1.0000
  12.000   1.2838   0.03168   0.02663  -0.0133   0.0052   1.0000
  12.250   1.2925   0.03276   0.02783  -0.0118   0.0049   1.0000
  12.500   1.2951   0.03447   0.02967  -0.0099   0.0047   1.0000
  12.750   1.3004   0.03598   0.03128  -0.0087   0.0044   1.0000
  13.000   1.3027   0.03787   0.03329  -0.0076   0.0043   1.0000
  13.250   1.3037   0.04005   0.03559  -0.0069   0.0041   1.0000
  13.500   1.3008   0.04281   0.03850  -0.0065   0.0041   1.0000
  13.750   1.2976   0.04586   0.04167  -0.0067   0.0039   1.0000
  14.000   1.2880   0.05000   0.04595  -0.0076   0.0038   1.0000
  14.250   1.2757   0.05491   0.05104  -0.0093   0.0038   1.0000
  14.500   1.2667   0.05976   0.05606  -0.0114   0.0037   1.0000
  14.750   1.2511   0.06602   0.06250  -0.0144   0.0037   1.0000
  15.000   1.2368   0.07244   0.06909  -0.0179   0.0037   1.0000
  15.250   1.2212   0.07952   0.07634  -0.0219   0.0037   1.0000
  15.500   1.2014   0.08772   0.08470  -0.0266   0.0036   1.0000
  15.750   1.1817   0.09632   0.09346  -0.0316   0.0037   1.0000
  16.000   1.1596   0.10579   0.10307  -0.0371   0.0037   1.0000
  16.250   1.1409   0.11496   0.11238  -0.0425   0.0036   1.0000
  16.500   1.1179   0.12529   0.12283  -0.0484   0.0037   1.0000
  16.750   1.0971   0.13553   0.13318  -0.0543   0.0037   1.0000
  17.000   1.0746   0.14677   0.14458  -0.0607   0.0039   1.0000
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