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AIRFOIL PROFILE12A 9.00% (rg12a-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: AIRFOIL PROFILE12A 9.00% (rg12a-il)
Reynolds number: 200,000
Max Cl/Cd: 62.21 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg12a-il-200000-n5.txt
Download as CSV file: xf-rg12a-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AIRFOIL PROFILE12A 9.00%                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4865   0.09534   0.09167  -0.0248   1.0000   0.0140
  -9.500  -0.4881   0.09123   0.08760  -0.0263   1.0000   0.0138
  -9.250  -0.4904   0.08715   0.08356  -0.0278   1.0000   0.0135
  -9.000  -0.4949   0.08267   0.07914  -0.0296   1.0000   0.0132
  -8.750  -0.5011   0.07806   0.07458  -0.0318   1.0000   0.0129
  -8.500  -0.5119   0.07296   0.06955  -0.0347   1.0000   0.0127
  -8.250  -0.5285   0.06802   0.06465  -0.0377   1.0000   0.0125
  -8.000  -0.5394   0.06277   0.05936  -0.0396   1.0000   0.0123
  -7.750  -0.5499   0.05715   0.05363  -0.0405   1.0000   0.0120
  -7.500  -0.5577   0.05142   0.04772  -0.0403   1.0000   0.0116
  -7.250  -0.5681   0.04348   0.03938  -0.0391   1.0000   0.0109
  -7.000  -0.5725   0.03594   0.03113  -0.0369   1.0000   0.0103
  -6.750  -0.5634   0.03233   0.02707  -0.0352   1.0000   0.0102
  -6.500  -0.5513   0.02913   0.02342  -0.0336   1.0000   0.0102
  -6.250  -0.5360   0.02644   0.02032  -0.0322   1.0000   0.0102
  -6.000  -0.5185   0.02413   0.01764  -0.0309   1.0000   0.0104
  -5.750  -0.4992   0.02226   0.01547  -0.0297   1.0000   0.0106
  -5.500  -0.4723   0.02062   0.01354  -0.0300   0.9985   0.0110
  -5.250  -0.4393   0.01913   0.01182  -0.0313   0.9956   0.0116
  -5.000  -0.4066   0.01787   0.01038  -0.0325   0.9925   0.0125
  -4.750  -0.3737   0.01700   0.00934  -0.0337   0.9887   0.0142
  -4.500  -0.3407   0.01583   0.00808  -0.0351   0.9853   0.0162
  -4.250  -0.3077   0.01500   0.00716  -0.0364   0.9814   0.0180
  -4.000  -0.2757   0.01431   0.00633  -0.0373   0.9762   0.0208
  -3.750  -0.2412   0.01364   0.00565  -0.0389   0.9721   0.0292
  -3.500  -0.2096   0.01297   0.00506  -0.0398   0.9663   0.0525
  -3.250  -0.1766   0.01240   0.00465  -0.0412   0.9607   0.0919
  -3.000  -0.1435   0.01170   0.00430  -0.0428   0.9554   0.1713
  -2.750  -0.1131   0.01102   0.00399  -0.0438   0.9481   0.2696
  -2.500  -0.0793   0.01032   0.00371  -0.0454   0.9430   0.3898
  -2.250  -0.0518   0.00959   0.00351  -0.0455   0.9344   0.5321
  -2.000  -0.0237   0.00912   0.00362  -0.0450   0.9273   0.7013
  -1.750   0.0071   0.00903   0.00358  -0.0451   0.9185   0.7576
  -1.500   0.0377   0.00896   0.00350  -0.0453   0.9084   0.7860
  -1.250   0.0698   0.00889   0.00340  -0.0457   0.8985   0.8085
  -1.000   0.1025   0.00883   0.00329  -0.0462   0.8876   0.8279
  -0.750   0.1338   0.00877   0.00319  -0.0465   0.8743   0.8445
  -0.500   0.1642   0.00873   0.00310  -0.0465   0.8592   0.8595
  -0.250   0.1930   0.00870   0.00302  -0.0462   0.8421   0.8737
   0.000   0.2208   0.00869   0.00296  -0.0457   0.8234   0.8880
   0.250   0.2482   0.00869   0.00289  -0.0451   0.8038   0.9014
   0.500   0.2751   0.00870   0.00284  -0.0445   0.7823   0.9116
   0.750   0.3032   0.00874   0.00278  -0.0442   0.7605   0.9194
   1.000   0.3307   0.00879   0.00274  -0.0439   0.7376   0.9271
   1.250   0.3592   0.00886   0.00272  -0.0439   0.7145   0.9334
   1.500   0.3874   0.00896   0.00272  -0.0439   0.6915   0.9406
   1.750   0.4169   0.00906   0.00274  -0.0441   0.6679   0.9470
   2.000   0.4464   0.00918   0.00277  -0.0445   0.6441   0.9544
   2.500   0.5077   0.00947   0.00291  -0.0457   0.5939   0.9694
   2.750   0.5399   0.00964   0.00300  -0.0467   0.5666   0.9775
   3.000   0.5717   0.00982   0.00310  -0.0478   0.5391   0.9873
   3.250   0.6028   0.01004   0.00325  -0.0487   0.5102   1.0000
   3.500   0.6237   0.01027   0.00340  -0.0474   0.4832   1.0000
   3.750   0.6459   0.01054   0.00357  -0.0465   0.4544   1.0000
   4.000   0.6688   0.01083   0.00377  -0.0457   0.4252   1.0000
   4.250   0.6921   0.01115   0.00402  -0.0450   0.3954   1.0000
   4.500   0.7154   0.01150   0.00427  -0.0443   0.3639   1.0000
   4.750   0.7387   0.01188   0.00455  -0.0436   0.3303   1.0000
   5.000   0.7618   0.01230   0.00487  -0.0429   0.2973   1.0000
   5.250   0.7849   0.01275   0.00525  -0.0422   0.2648   1.0000
   5.500   0.8071   0.01330   0.00564  -0.0415   0.2243   1.0000
   5.750   0.8289   0.01393   0.00608  -0.0407   0.1812   1.0000
   6.000   0.8503   0.01462   0.00658  -0.0400   0.1410   1.0000
   6.250   0.8719   0.01532   0.00712  -0.0392   0.1064   1.0000
   6.500   0.8932   0.01605   0.00775  -0.0384   0.0785   1.0000
   6.750   0.9145   0.01679   0.00841  -0.0376   0.0555   1.0000
   7.000   0.9353   0.01760   0.00917  -0.0366   0.0392   1.0000
   7.250   0.9555   0.01849   0.01005  -0.0356   0.0300   1.0000
   7.500   0.9765   0.01926   0.01095  -0.0345   0.0262   1.0000
   7.750   0.9959   0.02017   0.01194  -0.0334   0.0237   1.0000
   8.000   1.0131   0.02129   0.01319  -0.0319   0.0217   1.0000
   8.250   1.0324   0.02214   0.01419  -0.0307   0.0202   1.0000
   8.500   1.0503   0.02314   0.01532  -0.0294   0.0189   1.0000
   8.750   1.0669   0.02427   0.01658  -0.0279   0.0181   1.0000
   9.000   1.0827   0.02546   0.01790  -0.0264   0.0172   1.0000
   9.250   1.0973   0.02680   0.01935  -0.0248   0.0166   1.0000
   9.500   1.1096   0.02843   0.02109  -0.0230   0.0157   1.0000
   9.750   1.1212   0.03032   0.02314  -0.0211   0.0148   1.0000
  10.000   1.1351   0.03167   0.02469  -0.0196   0.0140   1.0000
  10.250   1.1456   0.03341   0.02669  -0.0176   0.0135   1.0000
  10.500   1.1536   0.03529   0.02880  -0.0153   0.0130   1.0000
  10.750   1.1593   0.03721   0.03095  -0.0130   0.0124   1.0000
  11.000   1.1629   0.03892   0.03285  -0.0108   0.0118   1.0000
  11.250   1.1649   0.04071   0.03480  -0.0087   0.0112   1.0000
  11.500   1.1651   0.04257   0.03677  -0.0070   0.0107   1.0000
  11.750   1.1620   0.04508   0.03944  -0.0055   0.0103   1.0000
  12.000   1.1516   0.04877   0.04336  -0.0042   0.0100   1.0000
  12.250   1.1397   0.05277   0.04760  -0.0037   0.0098   1.0000
  12.500   1.1296   0.05660   0.05169  -0.0041   0.0097   1.0000
  12.750   1.1174   0.06115   0.05649  -0.0053   0.0096   1.0000
  13.000   1.1033   0.06642   0.06200  -0.0075   0.0096   1.0000
  13.250   1.0878   0.07239   0.06818  -0.0107   0.0095   1.0000
  13.500   1.0711   0.07915   0.07514  -0.0146   0.0096   1.0000
  13.750   1.0531   0.08669   0.08286  -0.0193   0.0096   1.0000
  14.000   1.0343   0.09500   0.09133  -0.0248   0.0096   1.0000
  14.250   1.0142   0.10422   0.10070  -0.0307   0.0097   1.0000
  14.500   0.9932   0.11433   0.11094  -0.0371   0.0098   1.0000
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