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TsAGI R-3a (12%) (tsagi-r-3a-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: TsAGI R-3a (12%) (tsagi-r-3a-il)
Reynolds number: 50,000
Max Cl/Cd: 25.75 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-tsagi-r-3a-il-50000-n5.txt
Download as CSV file: xf-tsagi-r-3a-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: TsAGI R-3a (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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4269   0.09668   0.09017  -0.0046   1.0045   0.0641
  -8.250  -0.4222   0.09267   0.08622  -0.0063   1.0045   0.0623
  -7.750  -0.4330   0.08021   0.07384  -0.0183   1.0045   0.0569
  -7.500  -0.4277   0.07598   0.06963  -0.0206   1.0045   0.0561
  -7.250  -0.4235   0.07136   0.06500  -0.0232   1.0045   0.0553
  -7.000  -0.4191   0.06651   0.06009  -0.0258   1.0045   0.0544
  -6.750  -0.4137   0.06161   0.05505  -0.0281   1.0045   0.0537
  -6.500  -0.4061   0.05699   0.05025  -0.0298   1.0045   0.0536
  -6.250  -0.3959   0.05286   0.04590  -0.0308   1.0045   0.0539
  -6.000  -0.3837   0.04902   0.04180  -0.0313   1.0045   0.0546
  -5.750  -0.3700   0.04540   0.03786  -0.0313   1.0045   0.0554
  -5.500  -0.3551   0.04206   0.03414  -0.0310   1.0045   0.0560
  -5.250  -0.3393   0.03906   0.03079  -0.0303   1.0045   0.0565
  -5.000  -0.3082   0.03575   0.02694  -0.0321   0.9813   0.0572
  -4.750  -0.2651   0.03316   0.02410  -0.0356   0.9332   0.0589
  -4.500  -0.2236   0.03115   0.02175  -0.0382   0.8813   0.0626
  -4.250  -0.1874   0.02933   0.01946  -0.0391   0.8313   0.0667
  -4.000  -0.1578   0.02810   0.01793  -0.0386   0.7861   0.0707
  -3.750  -0.1310   0.02699   0.01645  -0.0374   0.7492   0.0761
  -3.500  -0.1052   0.02621   0.01539  -0.0363   0.7188   0.0839
  -3.250  -0.0796   0.02553   0.01454  -0.0353   0.6947   0.0942
  -3.000  -0.0533   0.02490   0.01372  -0.0344   0.6747   0.1081
  -2.750  -0.0262   0.02423   0.01286  -0.0337   0.6567   0.1244
  -2.500  -0.0005   0.02351   0.01212  -0.0330   0.6396   0.1455
  -2.250   0.0245   0.02277   0.01141  -0.0322   0.6230   0.1803
  -2.000   0.0485   0.02191   0.01083  -0.0315   0.6072   0.2466
  -1.750   0.0663   0.02046   0.01055  -0.0297   0.5930   0.4673
  -1.500   0.1067   0.01950   0.01071  -0.0279   0.5766   0.9008
  -1.250   0.1732   0.01960   0.01026  -0.0344   0.5591   0.9955
  -1.000   0.1969   0.01976   0.01006  -0.0337   0.5477   0.9955
  -0.750   0.2211   0.01995   0.00998  -0.0331   0.5361   0.9955
  -0.500   0.2451   0.02017   0.00986  -0.0323   0.5262   0.9955
  -0.250   0.2694   0.02040   0.00988  -0.0317   0.5151   0.9955
   0.000   0.2938   0.02067   0.00990  -0.0310   0.5054   0.9955
   0.250   0.3184   0.02094   0.00996  -0.0304   0.4953   0.9955
   0.500   0.3434   0.02125   0.01009  -0.0299   0.4853   0.9955
   0.750   0.3683   0.02156   0.01018  -0.0293   0.4760   0.9955
   1.000   0.3934   0.02192   0.01042  -0.0288   0.4660   0.9955
   1.250   0.4185   0.02226   0.01053  -0.0281   0.4575   0.9955
   1.500   0.4435   0.02267   0.01087  -0.0277   0.4471   0.9955
   1.750   0.4687   0.02303   0.01100  -0.0270   0.4393   0.9955
   2.000   0.4936   0.02352   0.01146  -0.0267   0.4290   0.9955
   2.250   0.5189   0.02393   0.01167  -0.0261   0.4219   0.9955
   2.500   0.5437   0.02453   0.01229  -0.0258   0.4125   0.9955
   2.750   0.5690   0.02499   0.01261  -0.0252   0.4055   0.9955
   3.000   0.5935   0.02563   0.01327  -0.0249   0.3969   0.9955
   3.250   0.6184   0.02615   0.01370  -0.0244   0.3897   0.9955
   3.500   0.6430   0.02678   0.01430  -0.0240   0.3828   0.9955
   3.750   0.6671   0.02749   0.01506  -0.0237   0.3755   0.9955
   4.000   0.6923   0.02802   0.01548  -0.0232   0.3706   0.9955
   4.250   0.7153   0.02894   0.01651  -0.0229   0.3636   0.9955
   4.500   0.7391   0.02963   0.01722  -0.0225   0.3575   0.9955
   4.750   0.7644   0.03007   0.01756  -0.0220   0.3531   0.9955
   5.000   0.7852   0.03126   0.01895  -0.0217   0.3460   0.9955
   5.250   0.8085   0.03199   0.01969  -0.0212   0.3408   0.9955
   5.500   0.8339   0.03238   0.02000  -0.0207   0.3368   0.9955
   5.750   0.8519   0.03383   0.02170  -0.0203   0.3295   0.9955
   6.000   0.8749   0.03445   0.02233  -0.0198   0.3242   0.9955
   6.250   0.8984   0.03501   0.02286  -0.0192   0.3197   0.9955
   6.500   0.9147   0.03651   0.02461  -0.0187   0.3127   0.9955
   6.750   0.9380   0.03701   0.02509  -0.0181   0.3080   0.9955
   7.000   0.9577   0.03800   0.02616  -0.0175   0.3030   0.9955
   7.250   0.9724   0.03960   0.02795  -0.0169   0.2968   0.9955
   7.500   0.9954   0.04008   0.02844  -0.0162   0.2926   0.9955
   7.750   1.0130   0.04128   0.02972  -0.0156   0.2879   0.9955
   8.000   1.0214   0.04348   0.03215  -0.0149   0.2817   0.9955
   8.250   1.0433   0.04404   0.03274  -0.0142   0.2776   0.9955
   8.500   1.0653   0.04465   0.03334  -0.0135   0.2739   0.9955
   8.750   1.0522   0.04904   0.03811  -0.0128   0.2670   0.9955
   9.000   1.0681   0.05016   0.03928  -0.0120   0.2627   0.9955
   9.250   1.0991   0.04978   0.03885  -0.0112   0.2597   0.9955
   9.500   0.9761   0.06642   0.05597  -0.0150   0.2492   0.9955
   9.750   0.9905   0.06763   0.05720  -0.0144   0.2458   0.9955
  10.000   1.0292   0.06548   0.05507  -0.0117   0.2440   0.9955
  10.500   0.8742   0.09809   0.08778  -0.0291   0.2231   0.9955
  10.750   0.8613   0.10412   0.09384  -0.0314   0.2182   0.9955
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