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RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RG 12A-1.8/9.0 AIRFOIL (rg12a189-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-rg12a189-il-200000-n5.txt
Download as CSV file: xf-rg12a189-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3926   0.09361   0.09012  -0.0274   1.0000   0.0142
 -10.000  -0.3944   0.08947   0.08601  -0.0282   1.0000   0.0139
  -9.750  -0.4872   0.09500   0.09134  -0.0252   1.0000   0.0141
  -9.500  -0.4886   0.09108   0.08745  -0.0264   1.0000   0.0138
  -9.250  -0.4910   0.08697   0.08338  -0.0279   1.0000   0.0135
  -9.000  -0.4947   0.08271   0.07917  -0.0296   1.0000   0.0132
  -8.750  -0.5020   0.07784   0.07436  -0.0319   1.0000   0.0130
  -8.500  -0.5112   0.07312   0.06970  -0.0346   1.0000   0.0127
  -8.250  -0.5283   0.06806   0.06469  -0.0377   1.0000   0.0126
  -8.000  -0.5404   0.06255   0.05913  -0.0397   1.0000   0.0123
  -7.750  -0.5507   0.05696   0.05344  -0.0405   1.0000   0.0119
  -7.500  -0.5583   0.05127   0.04756  -0.0403   1.0000   0.0115
  -7.250  -0.5673   0.04381   0.03973  -0.0391   1.0000   0.0109
  -7.000  -0.5726   0.03599   0.03120  -0.0369   1.0000   0.0103
  -6.750  -0.5637   0.03229   0.02703  -0.0352   1.0000   0.0102
  -6.500  -0.5514   0.02912   0.02341  -0.0336   1.0000   0.0102
  -6.250  -0.5361   0.02642   0.02028  -0.0322   1.0000   0.0102
  -6.000  -0.5185   0.02415   0.01766  -0.0309   1.0000   0.0103
  -5.750  -0.4993   0.02225   0.01546  -0.0297   1.0000   0.0106
  -5.500  -0.4727   0.02060   0.01353  -0.0299   0.9986   0.0110
  -5.250  -0.4398   0.01913   0.01182  -0.0312   0.9957   0.0115
  -5.000  -0.4072   0.01787   0.01038  -0.0324   0.9927   0.0124
  -4.750  -0.3742   0.01701   0.00936  -0.0336   0.9888   0.0142
  -4.500  -0.3411   0.01585   0.00810  -0.0350   0.9853   0.0161
  -4.250  -0.3079   0.01500   0.00715  -0.0363   0.9814   0.0180
  -4.000  -0.2757   0.01430   0.00632  -0.0373   0.9761   0.0210
  -3.750  -0.2410   0.01364   0.00564  -0.0389   0.9720   0.0293
  -3.500  -0.2096   0.01297   0.00506  -0.0398   0.9662   0.0526
  -3.250  -0.1766   0.01240   0.00465  -0.0412   0.9606   0.0922
  -3.000  -0.1437   0.01170   0.00430  -0.0427   0.9554   0.1720
  -2.750  -0.1134   0.01103   0.00400  -0.0437   0.9482   0.2693
  -2.500  -0.0793   0.01032   0.00371  -0.0454   0.9433   0.3898
  -2.250  -0.0520   0.00959   0.00351  -0.0455   0.9345   0.5327
  -2.000  -0.0238   0.00912   0.00363  -0.0450   0.9275   0.7024
  -1.750   0.0069   0.00903   0.00358  -0.0451   0.9186   0.7571
  -1.500   0.0375   0.00896   0.00350  -0.0452   0.9085   0.7862
  -1.250   0.0698   0.00889   0.00340  -0.0457   0.8987   0.8084
  -1.000   0.1026   0.00883   0.00329  -0.0462   0.8879   0.8278
  -0.750   0.1337   0.00878   0.00319  -0.0465   0.8745   0.8446
  -0.500   0.1642   0.00873   0.00311  -0.0465   0.8595   0.8595
  -0.250   0.1928   0.00870   0.00302  -0.0462   0.8422   0.8738
   0.000   0.2206   0.00868   0.00296  -0.0457   0.8235   0.8880
   0.250   0.2481   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   0.00277  -0.0442   0.7605   0.9194
   1.000   0.3307   0.00879   0.00274  -0.0439   0.7374   0.9271
   1.250   0.3592   0.00886   0.00271  -0.0439   0.7145   0.9334
   1.500   0.3875   0.00896   0.00272  -0.0439   0.6914   0.9406
   1.750   0.4169   0.00906   0.00273  -0.0441   0.6678   0.9470
   2.000   0.4465   0.00918   0.00277  -0.0445   0.6439   0.9544
   2.250   0.4771   0.00932   0.00284  -0.0451   0.6192   0.9614
   2.500   0.5077   0.00947   0.00291  -0.0457   0.5934   0.9694
   2.750   0.5399   0.00964   0.00299  -0.0468   0.5666   0.9775
   3.000   0.5718   0.00982   0.00310  -0.0478   0.5390   0.9874
   3.250   0.6026   0.01004   0.00325  -0.0486   0.5099   1.0000
   3.500   0.6236   0.01027   0.00340  -0.0474   0.4830   1.0000
   3.750   0.6459   0.01054   0.00357  -0.0465   0.4547   1.0000
   4.000   0.6689   0.01083   0.00377  -0.0457   0.4252   1.0000
   4.250   0.6921   0.01115   0.00402  -0.0450   0.3952   1.0000
   4.500   0.7154   0.01150   0.00427  -0.0443   0.3638   1.0000
   4.750   0.7388   0.01188   0.00455  -0.0436   0.3303   1.0000
   5.000   0.7619   0.01230   0.00487  -0.0429   0.2971   1.0000
   5.250   0.7851   0.01274   0.00525  -0.0423   0.2651   1.0000
   5.500   0.8072   0.01330   0.00564  -0.0415   0.2240   1.0000
   5.750   0.8290   0.01394   0.00608  -0.0408   0.1803   1.0000
   6.000   0.8505   0.01462   0.00658  -0.0400   0.1409   1.0000
   6.250   0.8721   0.01532   0.00712  -0.0393   0.1065   1.0000
   6.500   0.8935   0.01604   0.00775  -0.0385   0.0789   1.0000
   6.750   0.9148   0.01680   0.00841  -0.0376   0.0555   1.0000
   7.000   0.9356   0.01760   0.00917  -0.0367   0.0393   1.0000
   7.250   0.9559   0.01848   0.01005  -0.0356   0.0302   1.0000
   7.500   0.9768   0.01926   0.01096  -0.0346   0.0262   1.0000
   7.750   0.9963   0.02017   0.01195  -0.0334   0.0237   1.0000
   8.000   1.0135   0.02128   0.01319  -0.0320   0.0217   1.0000
   8.250   1.0328   0.02215   0.01420  -0.0308   0.0202   1.0000
   8.500   1.0506   0.02315   0.01533  -0.0295   0.0190   1.0000
   8.750   1.0673   0.02428   0.01659  -0.0280   0.0180   1.0000
   9.000   1.0831   0.02547   0.01791  -0.0265   0.0173   1.0000
   9.250   1.0977   0.02681   0.01936  -0.0249   0.0165   1.0000
   9.500   1.1100   0.02846   0.02112  -0.0231   0.0157   1.0000
   9.750   1.1216   0.03038   0.02320  -0.0212   0.0148   1.0000
  10.000   1.1356   0.03170   0.02473  -0.0197   0.0141   1.0000
  10.250   1.1462   0.03343   0.02671  -0.0177   0.0135   1.0000
  10.500   1.1542   0.03533   0.02884  -0.0155   0.0130   1.0000
  10.750   1.1598   0.03719   0.03093  -0.0132   0.0124   1.0000
  11.000   1.1633   0.03901   0.03294  -0.0109   0.0118   1.0000
  11.250   1.1655   0.04069   0.03478  -0.0089   0.0112   1.0000
  11.500   1.1655   0.04267   0.03689  -0.0071   0.0108   1.0000
  11.750   1.1621   0.04518   0.03954  -0.0056   0.0103   1.0000
  12.000   1.1512   0.04892   0.04350  -0.0043   0.0100   1.0000
  12.250   1.1400   0.05280   0.04764  -0.0039   0.0098   1.0000
  12.500   1.1298   0.05669   0.05178  -0.0042   0.0097   1.0000
  12.750   1.1177   0.06122   0.05656  -0.0055   0.0096   1.0000
  13.000   1.1033   0.06652   0.06210  -0.0077   0.0096   1.0000
  13.250   1.0877   0.07254   0.06833  -0.0108   0.0096   1.0000
  13.500   1.0711   0.07925   0.07524  -0.0148   0.0096   1.0000
  13.750   1.0532   0.08681   0.08299  -0.0196   0.0096   1.0000
  14.000   1.0341   0.09521   0.09156  -0.0250   0.0096   1.0000
  14.250   1.0147   0.10422   0.10070  -0.0308   0.0097   1.0000
  14.500   0.9943   0.11415   0.11076  -0.0371   0.0098   1.0000
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