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RG-12 (rg12-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RG-12 (rg12-il)
Reynolds number: 500,000
Max Cl/Cd: 82.65 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg12-il-500000.txt
Download as CSV file: xf-rg12-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5091   0.08558   0.08331  -0.0297   1.0000   0.0194
  -9.250  -0.5133   0.07970   0.07746  -0.0332   1.0000   0.0194
  -9.000  -0.5229   0.07051   0.06827  -0.0413   1.0000   0.0194
  -8.750  -0.5398   0.06545   0.06317  -0.0444   1.0000   0.0194
  -8.500  -0.5611   0.06222   0.05987  -0.0433   1.0000   0.0194
  -8.250  -0.5740   0.05855   0.05609  -0.0423   1.0000   0.0194
  -8.000  -0.6149   0.04976   0.04707  -0.0405   1.0000   0.0200
  -7.750  -0.6228   0.04556   0.04271  -0.0385   1.0000   0.0204
  -7.500  -0.6223   0.04256   0.03958  -0.0365   1.0000   0.0209
  -7.250  -0.6152   0.04064   0.03760  -0.0347   1.0000   0.0214
  -7.000  -0.6090   0.03822   0.03502  -0.0327   1.0000   0.0219
  -6.250  -0.5861   0.02650   0.02216  -0.0249   1.0000   0.0179
  -6.000  -0.5679   0.01994   0.01460  -0.0228   0.9993   0.0133
  -5.750  -0.5338   0.01861   0.01307  -0.0243   0.9971   0.0130
  -5.500  -0.5002   0.01697   0.01123  -0.0257   0.9951   0.0129
  -5.250  -0.4701   0.01443   0.00842  -0.0264   0.9932   0.0134
  -5.000  -0.4386   0.01305   0.00691  -0.0274   0.9902   0.0142
  -4.750  -0.4042   0.01231   0.00610  -0.0290   0.9872   0.0156
  -4.500  -0.3678   0.01173   0.00546  -0.0309   0.9847   0.0173
  -4.250  -0.3298   0.01128   0.00493  -0.0331   0.9827   0.0192
  -4.000  -0.2991   0.01057   0.00421  -0.0338   0.9776   0.0273
  -3.750  -0.2643   0.00985   0.00369  -0.0354   0.9739   0.0701
  -3.500  -0.2269   0.00942   0.00339  -0.0377   0.9713   0.1088
  -3.250  -0.1937   0.00887   0.00313  -0.0392   0.9671   0.1770
  -3.000  -0.1617   0.00822   0.00288  -0.0405   0.9619   0.2780
  -2.750  -0.1264   0.00746   0.00263  -0.0425   0.9587   0.4134
  -2.500  -0.0922   0.00676   0.00241  -0.0442   0.9552   0.5486
  -2.250  -0.0642   0.00624   0.00234  -0.0441   0.9479   0.6794
  -2.000  -0.0290   0.00607   0.00228  -0.0454   0.9435   0.7370
  -1.750   0.0008   0.00598   0.00221  -0.0455   0.9343   0.7639
  -1.500   0.0338   0.00590   0.00212  -0.0462   0.9264   0.7838
  -1.250   0.0656   0.00584   0.00203  -0.0468   0.9163   0.7999
  -1.000   0.0950   0.00581   0.00198  -0.0468   0.9036   0.8137
  -0.750   0.1238   0.00579   0.00194  -0.0466   0.8896   0.8256
  -0.500   0.1518   0.00579   0.00189  -0.0463   0.8742   0.8361
  -0.250   0.1788   0.00582   0.00186  -0.0459   0.8571   0.8464
   0.000   0.2050   0.00585   0.00185  -0.0452   0.8389   0.8560
   0.250   0.2308   0.00589   0.00184  -0.0445   0.8200   0.8648
   0.500   0.2568   0.00595   0.00183  -0.0438   0.8001   0.8736
   0.750   0.2817   0.00600   0.00183  -0.0429   0.7794   0.8819
   1.000   0.3064   0.00607   0.00184  -0.0420   0.7582   0.8908
   1.250   0.3310   0.00616   0.00186  -0.0411   0.7360   0.9004
   1.500   0.3546   0.00622   0.00189  -0.0399   0.7132   0.9089
   1.750   0.3783   0.00631   0.00191  -0.0388   0.6897   0.9177
   2.000   0.4019   0.00641   0.00194  -0.0377   0.6653   0.9267
   2.250   0.4254   0.00651   0.00198  -0.0366   0.6398   0.9348
   2.500   0.4494   0.00662   0.00202  -0.0357   0.6137   0.9436
   2.750   0.4744   0.00674   0.00207  -0.0350   0.5872   0.9519
   3.000   0.5015   0.00689   0.00214  -0.0348   0.5594   0.9601
   3.250   0.5298   0.00706   0.00222  -0.0350   0.5294   0.9692
   3.500   0.5628   0.00729   0.00235  -0.0362   0.4957   0.9755
   3.750   0.5954   0.00752   0.00248  -0.0375   0.4609   0.9832
   4.000   0.6306   0.00780   0.00263  -0.0393   0.4247   0.9889
   4.250   0.6652   0.00810   0.00281  -0.0411   0.3864   0.9957
   4.500   0.6926   0.00838   0.00300  -0.0414   0.3535   1.0000
   4.750   0.7119   0.00868   0.00318  -0.0400   0.3209   1.0000
   5.000   0.7342   0.00905   0.00340  -0.0392   0.2850   1.0000
   5.250   0.7570   0.00949   0.00367  -0.0385   0.2446   1.0000
   5.500   0.7797   0.00998   0.00397  -0.0378   0.2016   1.0000
   5.750   0.8027   0.01048   0.00432  -0.0371   0.1652   1.0000
   6.000   0.8260   0.01096   0.00468  -0.0365   0.1350   1.0000
   6.250   0.8492   0.01146   0.00507  -0.0359   0.1076   1.0000
   6.500   0.8721   0.01201   0.00550  -0.0352   0.0834   1.0000
   6.750   0.8943   0.01263   0.00600  -0.0345   0.0601   1.0000
   7.000   0.9166   0.01325   0.00654  -0.0337   0.0416   1.0000
   7.250   0.9382   0.01395   0.00721  -0.0328   0.0298   1.0000
   7.500   0.9602   0.01461   0.00792  -0.0318   0.0238   1.0000
   7.750   0.9791   0.01561   0.00896  -0.0304   0.0180   1.0000
   8.000   1.0022   0.01609   0.00950  -0.0298   0.0153   1.0000
   8.250   1.0204   0.01711   0.01057  -0.0283   0.0127   1.0000
   8.500   1.0374   0.01827   0.01187  -0.0266   0.0113   1.0000
   8.750   1.0559   0.01921   0.01292  -0.0252   0.0103   1.0000
   9.000   1.0738   0.02019   0.01398  -0.0238   0.0094   1.0000
   9.250   1.0900   0.02131   0.01521  -0.0223   0.0088   1.0000
   9.500   1.1027   0.02289   0.01692  -0.0202   0.0084   1.0000
   9.750   1.1124   0.02502   0.01923  -0.0178   0.0081   1.0000
  10.000   1.1202   0.02777   0.02222  -0.0154   0.0079   1.0000
  10.250   1.1264   0.03085   0.02559  -0.0129   0.0078   1.0000
  10.500   1.1358   0.03237   0.02729  -0.0108   0.0077   1.0000
  10.750   1.1412   0.03380   0.02891  -0.0080   0.0076   1.0000
  11.000   1.1459   0.03495   0.03024  -0.0053   0.0074   1.0000
  11.250   1.1449   0.03695   0.03244  -0.0024   0.0073   1.0000
  11.500   1.1392   0.03945   0.03517   0.0003   0.0072   1.0000
  11.750   1.1320   0.04209   0.03802   0.0025   0.0071   1.0000
  12.000   1.1201   0.04544   0.04160   0.0041   0.0071   1.0000
  12.250   1.1081   0.04901   0.04538   0.0047   0.0071   1.0000
  12.500   1.0932   0.05332   0.04989   0.0043   0.0071   1.0000
  12.750   1.0773   0.05828   0.05505   0.0028   0.0071   1.0000
  13.000   1.0601   0.06404   0.06099   0.0000   0.0072   1.0000
  13.250   1.0377   0.07144   0.06858  -0.0043   0.0072   1.0000
  13.500   1.0197   0.07881   0.07611  -0.0091   0.0073   1.0000
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