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RG-12 (rg12-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: RG-12 (rg12-il)
Reynolds number: 50,000
Max Cl/Cd: 32.94 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg12-il-50000.txt
Download as CSV file: xf-rg12-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG-12                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4929   0.10431   0.09750  -0.0091   1.0000   0.2716
  -8.500  -0.4887   0.10108   0.09425  -0.0085   1.0000   0.2844
  -8.250  -0.4841   0.09770   0.09093  -0.0078   1.0000   0.2982
  -8.000  -0.4888   0.09507   0.08839  -0.0071   1.0000   0.3128
  -7.750  -0.4646   0.09062   0.08392  -0.0046   1.0000   0.3378
  -7.500  -0.4803   0.08889   0.08234  -0.0035   1.0000   0.3549
  -7.250  -0.4621   0.08453   0.07798  -0.0020   1.0000   0.3719
  -6.750  -0.5631   0.06301   0.05616  -0.0339   1.0000   0.1460
  -6.500  -0.5506   0.05701   0.05003  -0.0337   1.0000   0.1263
  -6.250  -0.5459   0.05149   0.04402  -0.0339   1.0000   0.1142
  -6.000  -0.5390   0.04631   0.03795  -0.0333   1.0000   0.1051
  -5.750  -0.5246   0.04284   0.03393  -0.0320   1.0000   0.1044
  -5.500  -0.5081   0.03972   0.03092  -0.0309   1.0000   0.1096
  -5.250  -0.4901   0.03663   0.02732  -0.0297   1.0000   0.1122
  -5.000  -0.4694   0.03354   0.02370  -0.0283   1.0000   0.1140
  -4.750  -0.4468   0.03079   0.02033  -0.0269   1.0000   0.1189
  -4.500  -0.4255   0.02865   0.01813  -0.0257   1.0000   0.1344
  -4.250  -0.4022   0.02649   0.01591  -0.0243   1.0000   0.1527
  -4.000  -0.3793   0.02461   0.01400  -0.0228   1.0000   0.1859
  -3.750  -0.3573   0.02272   0.01244  -0.0212   1.0000   0.2381
  -3.500  -0.3372   0.02053   0.01093  -0.0193   1.0000   0.3369
  -3.250  -0.3359   0.01793   0.01064  -0.0121   1.0000   0.6203
  -3.000  -0.0978   0.01980   0.01091  -0.0365   1.0000   1.0000
  -2.750  -0.0929   0.01932   0.01029  -0.0342   1.0000   1.0000
  -2.500  -0.0879   0.01896   0.00975  -0.0317   1.0000   1.0000
  -2.250  -0.0835   0.01866   0.00934  -0.0289   1.0000   1.0000
  -2.000  -0.0801   0.01843   0.00901  -0.0258   1.0000   1.0000
  -1.750  -0.0779   0.01825   0.00873  -0.0224   1.0000   1.0000
  -1.500  -0.0769   0.01810   0.00850  -0.0188   1.0000   1.0000
  -1.250  -0.0762   0.01798   0.00830  -0.0152   1.0000   1.0000
  -1.000  -0.0745   0.01791   0.00814  -0.0117   1.0000   1.0000
  -0.750  -0.0702   0.01790   0.00802  -0.0088   1.0000   1.0000
  -0.500  -0.0615   0.01798   0.00794  -0.0066   1.0000   1.0000
  -0.250  -0.0493   0.01813   0.00797  -0.0050   1.0000   1.0000
   0.000  -0.0351   0.01835   0.00807  -0.0039   1.0000   1.0000
   0.250  -0.0197   0.01863   0.00825  -0.0030   1.0000   1.0000
   0.500  -0.0036   0.01898   0.00851  -0.0023   1.0000   1.0000
   0.750   0.0127   0.01939   0.00882  -0.0017   1.0000   1.0000
   1.000   0.0292   0.01986   0.00923  -0.0013   1.0000   1.0000
   1.250   0.0456   0.02040   0.00972  -0.0010   1.0000   1.0000
   1.500   0.0618   0.02101   0.01030  -0.0008   1.0000   1.0000
   1.750   0.0777   0.02170   0.01096  -0.0007   1.0000   1.0000
   2.000   0.1295   0.02304   0.01233  -0.0074   0.9839   1.0000
   2.250   0.1877   0.02423   0.01358  -0.0147   0.9610   1.0000
   2.500   0.2437   0.02520   0.01466  -0.0212   0.9377   1.0000
   2.750   0.3032   0.02597   0.01556  -0.0278   0.9144   1.0000
   3.000   0.3555   0.02645   0.01622  -0.0327   0.8896   1.0000
   3.250   0.4064   0.02675   0.01674  -0.0368   0.8639   1.0000
   3.500   0.4608   0.02677   0.01699  -0.0408   0.8381   1.0000
   3.750   0.5187   0.02642   0.01693  -0.0446   0.8118   1.0000
   4.000   0.5707   0.02588   0.01671  -0.0468   0.7841   1.0000
   4.250   0.6170   0.02525   0.01633  -0.0475   0.7544   1.0000
   4.500   0.6601   0.02452   0.01581  -0.0472   0.7224   1.0000
   4.750   0.6916   0.02420   0.01569  -0.0454   0.6866   1.0000
   5.000   0.7229   0.02385   0.01541  -0.0433   0.6485   1.0000
   5.250   0.7490   0.02377   0.01535  -0.0408   0.6067   1.0000
   5.500   0.7715   0.02392   0.01547  -0.0380   0.5613   1.0000
   5.750   0.7937   0.02414   0.01557  -0.0351   0.5127   1.0000
   6.000   0.8123   0.02466   0.01602  -0.0322   0.4605   1.0000
   6.250   0.8298   0.02538   0.01653  -0.0292   0.4058   1.0000
   6.500   0.8460   0.02637   0.01726  -0.0264   0.3501   1.0000
   6.750   0.8616   0.02768   0.01829  -0.0237   0.2964   1.0000
   7.000   0.8776   0.02922   0.01949  -0.0214   0.2480   1.0000
   7.250   0.8951   0.03119   0.02128  -0.0194   0.2072   1.0000
   7.500   0.9128   0.03344   0.02348  -0.0176   0.1750   1.0000
   7.750   0.9313   0.03581   0.02578  -0.0160   0.1494   1.0000
   8.000   0.9500   0.03884   0.02921  -0.0144   0.1333   1.0000
   8.250   0.9654   0.04163   0.03224  -0.0127   0.1193   1.0000
   8.500   0.9838   0.04514   0.03584  -0.0115   0.1103   1.0000
   8.750   0.9897   0.04925   0.04069  -0.0090   0.1073   1.0000
   9.000   0.9925   0.05358   0.04558  -0.0067   0.1052   1.0000
   9.250   0.9945   0.05750   0.04986  -0.0048   0.1020   1.0000
   9.500   1.0009   0.06136   0.05380  -0.0035   0.0967   1.0000
   9.750   0.9898   0.06578   0.05863  -0.0015   0.0963   1.0000
  10.000   0.9763   0.07034   0.06349   0.0001   0.0965   1.0000
  10.250   0.9600   0.07498   0.06833   0.0013   0.0969   1.0000
  10.500   0.9458   0.07960   0.07306   0.0021   0.0975   1.0000
  10.750   0.8853   0.08812   0.08181  -0.0017   0.1099   1.0000
  11.000   0.8728   0.09447   0.08817  -0.0043   0.1108   1.0000
  11.250   0.8382   0.10704   0.10070  -0.0133   0.1245   1.0000
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