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RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: RG 12A-1.8/9.0 AIRFOIL (rg12a189-il)
Reynolds number: 1,000,000
Max Cl/Cd: 96.19 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg12a189-il-1000000.txt
Download as CSV file: xf-rg12a189-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4981   0.08256   0.08096  -0.0277   1.0000   0.0096
  -9.000  -0.5032   0.07765   0.07607  -0.0300   1.0000   0.0096
  -8.750  -0.5110   0.07241   0.07086  -0.0328   1.0000   0.0096
  -8.500  -0.5253   0.06689   0.06538  -0.0371   1.0000   0.0096
  -8.250  -0.5446   0.06163   0.06008  -0.0386   1.0000   0.0096
  -8.000  -0.5570   0.05577   0.05413  -0.0391   1.0000   0.0096
  -7.750  -0.5685   0.05019   0.04839  -0.0382   1.0000   0.0096
  -7.500  -0.5777   0.04544   0.04346  -0.0363   1.0000   0.0096
  -7.250  -0.5697   0.03990   0.03759  -0.0378   0.9986   0.0097
  -6.000  -0.4497   0.01575   0.01125  -0.0462   0.9865   0.0083
  -5.750  -0.4185   0.01335   0.00850  -0.0470   0.9852   0.0077
  -5.500  -0.3850   0.01205   0.00704  -0.0483   0.9841   0.0077
  -5.250  -0.3535   0.01118   0.00607  -0.0492   0.9821   0.0079
  -5.000  -0.3250   0.01051   0.00533  -0.0494   0.9782   0.0085
  -4.750  -0.2922   0.00996   0.00472  -0.0505   0.9756   0.0092
  -4.500  -0.2578   0.00943   0.00412  -0.0519   0.9736   0.0099
  -4.250  -0.2228   0.00874   0.00336  -0.0536   0.9719   0.0114
  -4.000  -0.1865   0.00839   0.00300  -0.0555   0.9706   0.0134
  -3.750  -0.1595   0.00799   0.00256  -0.0551   0.9646   0.0174
  -3.500  -0.1267   0.00747   0.00218  -0.0563   0.9609   0.0481
  -3.250  -0.0926   0.00711   0.00194  -0.0577   0.9577   0.0797
  -3.000  -0.0646   0.00676   0.00174  -0.0578   0.9497   0.1227
  -2.750  -0.0312   0.00629   0.00153  -0.0593   0.9438   0.1963
  -2.250   0.0275   0.00523   0.00118  -0.0605   0.9210   0.4235
  -2.000   0.0556   0.00474   0.00104  -0.0607   0.9061   0.5470
  -1.750   0.0821   0.00436   0.00099  -0.0604   0.8888   0.6720
  -1.500   0.1093   0.00433   0.00097  -0.0601   0.8694   0.7131
  -1.250   0.1361   0.00435   0.00095  -0.0597   0.8480   0.7378
  -1.000   0.1625   0.00441   0.00095  -0.0592   0.8256   0.7605
  -0.750   0.1889   0.00449   0.00094  -0.0587   0.8019   0.7732
  -0.500   0.2150   0.00457   0.00094  -0.0582   0.7774   0.7837
  -0.250   0.2412   0.00466   0.00095  -0.0577   0.7531   0.7936
   0.000   0.2675   0.00477   0.00096  -0.0573   0.7293   0.8028
   0.250   0.2935   0.00487   0.00099  -0.0568   0.7056   0.8111
   0.500   0.3200   0.00497   0.00102  -0.0564   0.6828   0.8188
   0.750   0.3462   0.00508   0.00106  -0.0559   0.6604   0.8266
   1.000   0.3726   0.00518   0.00109  -0.0556   0.6371   0.8341
   1.250   0.3989   0.00530   0.00115  -0.0552   0.6145   0.8418
   1.500   0.4249   0.00541   0.00120  -0.0547   0.5916   0.8499
   1.750   0.4512   0.00553   0.00126  -0.0543   0.5681   0.8590
   2.000   0.4768   0.00565   0.00133  -0.0538   0.5447   0.8667
   2.500   0.5290   0.00593   0.00148  -0.0531   0.4934   0.8786
   2.750   0.5553   0.00609   0.00156  -0.0528   0.4677   0.8843
   3.000   0.5812   0.00625   0.00165  -0.0524   0.4416   0.8899
   3.250   0.6067   0.00642   0.00177  -0.0520   0.4139   0.8963
   3.500   0.6319   0.00665   0.00189  -0.0515   0.3807   0.9031
   3.750   0.6570   0.00683   0.00202  -0.0510   0.3546   0.9107
   4.000   0.6808   0.00712   0.00217  -0.0502   0.3153   0.9196
   4.250   0.7039   0.00741   0.00235  -0.0493   0.2777   0.9309
   4.500   0.7262   0.00767   0.00252  -0.0482   0.2441   0.9454
   4.750   0.7501   0.00792   0.00269  -0.0475   0.2146   0.9653
   5.000   0.7816   0.00833   0.00293  -0.0486   0.1748   0.9882
   5.250   0.8089   0.00877   0.00321  -0.0488   0.1407   1.0000
   5.500   0.8339   0.00918   0.00349  -0.0486   0.1128   1.0000
   5.750   0.8584   0.00962   0.00380  -0.0482   0.0856   1.0000
   6.000   0.8825   0.01011   0.00415  -0.0477   0.0600   1.0000
   6.250   0.9051   0.01076   0.00463  -0.0470   0.0304   1.0000
   6.500   0.9289   0.01129   0.00510  -0.0463   0.0191   1.0000
   6.750   0.9531   0.01174   0.00556  -0.0458   0.0164   1.0000
   7.000   0.9762   0.01236   0.00628  -0.0449   0.0144   1.0000
   7.250   1.0007   0.01274   0.00670  -0.0445   0.0139   1.0000
   7.500   1.0248   0.01318   0.00719  -0.0439   0.0132   1.0000
   7.750   1.0480   0.01368   0.00777  -0.0432   0.0124   1.0000
   8.000   1.0707   0.01424   0.00839  -0.0425   0.0117   1.0000
   8.250   1.0927   0.01484   0.00904  -0.0416   0.0109   1.0000
   8.500   1.1101   0.01596   0.01027  -0.0400   0.0099   1.0000
   8.750   1.1267   0.01712   0.01156  -0.0383   0.0094   1.0000
   9.000   1.1491   0.01760   0.01210  -0.0376   0.0091   1.0000
   9.250   1.1701   0.01823   0.01282  -0.0366   0.0087   1.0000
   9.500   1.1901   0.01892   0.01358  -0.0356   0.0082   1.0000
   9.750   1.2102   0.01955   0.01428  -0.0346   0.0077   1.0000
  10.000   1.2307   0.02009   0.01484  -0.0337   0.0072   1.0000
  10.250   1.2480   0.02091   0.01571  -0.0324   0.0068   1.0000
  10.500   1.2468   0.02367   0.01871  -0.0285   0.0061   1.0000
  10.750   1.2650   0.02422   0.01933  -0.0273   0.0060   1.0000
  11.000   1.2813   0.02483   0.02004  -0.0258   0.0057   1.0000
  11.250   1.2928   0.02563   0.02093  -0.0235   0.0055   1.0000
  11.500   1.2994   0.02680   0.02224  -0.0207   0.0053   1.0000
  11.750   1.3080   0.02775   0.02328  -0.0184   0.0050   1.0000
  12.000   1.3156   0.02877   0.02440  -0.0161   0.0048   1.0000
  12.250   1.3215   0.02995   0.02568  -0.0138   0.0047   1.0000
  12.500   1.3267   0.03121   0.02702  -0.0118   0.0045   1.0000
  12.750   1.3288   0.03281   0.02873  -0.0098   0.0044   1.0000
  13.000   1.3270   0.03488   0.03092  -0.0079   0.0043   1.0000
  13.250   1.3322   0.03634   0.03244  -0.0069   0.0042   1.0000
  13.500   1.3230   0.03951   0.03579  -0.0057   0.0042   1.0000
  13.750   1.3124   0.04313   0.03956  -0.0053   0.0040   1.0000
  14.000   1.2983   0.04758   0.04417  -0.0059   0.0039   1.0000
  14.250   1.2838   0.05259   0.04936  -0.0073   0.0039   1.0000
  14.500   1.2632   0.05900   0.05597  -0.0099   0.0039   1.0000
  14.750   1.2272   0.06863   0.06587  -0.0148   0.0038   1.0000
  15.000   1.2276   0.07263   0.06994  -0.0171   0.0039   1.0000
  15.250   1.2112   0.07992   0.07738  -0.0213   0.0039   1.0000
  15.500   1.1930   0.08794   0.08554  -0.0261   0.0039   1.0000
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