Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

TsAGI R-3a (12%) (tsagi-r-3a-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: TsAGI R-3a (12%) (tsagi-r-3a-il)
Reynolds number: 500,000
Max Cl/Cd: 86.54 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-tsagi-r-3a-il-500000.txt
Download as CSV file: xf-tsagi-r-3a-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3487   0.09677   0.09480   0.0009   1.0045   0.0279
  -9.250  -0.3756   0.08623   0.08426  -0.0068   1.0045   0.0293
  -9.000  -0.3810   0.08043   0.07850  -0.0091   1.0045   0.0295
  -8.750  -0.3759   0.07734   0.07543  -0.0091   1.0045   0.0296
  -8.500  -0.3722   0.07399   0.07210  -0.0097   1.0045   0.0298
  -8.250  -0.3697   0.07042   0.06857  -0.0108   1.0045   0.0300
  -8.000  -0.3705   0.06624   0.06442  -0.0127   1.0045   0.0303
  -7.750  -0.3719   0.06094   0.05913  -0.0168   0.9555   0.0305
  -7.500  -0.3867   0.05413   0.05214  -0.0234   0.8773   0.0306
  -7.250  -0.3926   0.04857   0.04626  -0.0265   0.8063   0.0310
  -7.000  -0.3932   0.04288   0.04023  -0.0292   0.7457   0.0316
  -6.750  -0.4605   0.02453   0.01989  -0.0354   0.9424   0.0219
  -6.500  -0.4414   0.02262   0.01761  -0.0337   0.8601   0.0216
  -6.250  -0.4234   0.02084   0.01524  -0.0317   0.7679   0.0214
  -6.000  -0.4016   0.01936   0.01315  -0.0305   0.6806   0.0213
  -5.750  -0.3773   0.01816   0.01144  -0.0297   0.6116   0.0214
  -5.250  -0.3250   0.01648   0.00908  -0.0286   0.5350   0.0218
  -5.000  -0.2988   0.01552   0.00796  -0.0282   0.5161   0.0222
  -4.750  -0.2719   0.01494   0.00730  -0.0279   0.5031   0.0226
  -4.250  -0.2171   0.01405   0.00626  -0.0273   0.4832   0.0237
  -4.000  -0.1896   0.01366   0.00576  -0.0270   0.4751   0.0244
  -3.750  -0.1616   0.01336   0.00537  -0.0267   0.4685   0.0254
  -3.500  -0.1343   0.01294   0.00495  -0.0264   0.4620   0.0266
  -3.250  -0.1066   0.01269   0.00464  -0.0262   0.4562   0.0280
  -3.000  -0.0785   0.01239   0.00429  -0.0259   0.4515   0.0295
  -2.750  -0.0507   0.01206   0.00397  -0.0257   0.4465   0.0318
  -2.500  -0.0229   0.01178   0.00365  -0.0254   0.4419   0.0359
  -2.250   0.0049   0.01149   0.00335  -0.0252   0.4376   0.0451
  -2.000   0.0331   0.01124   0.00315  -0.0250   0.4335   0.0563
  -1.750   0.0612   0.01105   0.00301  -0.0248   0.4291   0.0698
  -1.500   0.0890   0.01085   0.00292  -0.0247   0.4247   0.1030
  -1.250   0.1169   0.01068   0.00286  -0.0246   0.4202   0.1437
  -1.000   0.1450   0.01043   0.00277  -0.0245   0.4157   0.1926
  -0.750   0.1717   0.00991   0.00269  -0.0244   0.4107   0.3237
  -0.500   0.1960   0.00915   0.00266  -0.0240   0.4059   0.5533
  -0.250   0.2189   0.00856   0.00271  -0.0227   0.4015   0.7360
   0.000   0.2407   0.00819   0.00277  -0.0207   0.3967   0.8645
   0.250   0.2715   0.00814   0.00280  -0.0205   0.3909   0.9402
   0.500   0.3144   0.00823   0.00280  -0.0232   0.3842   0.9738
   0.750   0.3576   0.00825   0.00277  -0.0261   0.3761   0.9888
   1.000   0.3984   0.00832   0.00273  -0.0286   0.3676   0.9955
   1.250   0.4247   0.00833   0.00269  -0.0281   0.3584   0.9955
   1.500   0.4509   0.00838   0.00266  -0.0276   0.3484   0.9955
   1.750   0.4772   0.00847   0.00264  -0.0272   0.3364   0.9955
   2.000   0.5036   0.00855   0.00264  -0.0268   0.3225   0.9955
   2.250   0.5300   0.00868   0.00267  -0.0263   0.3089   0.9955
   2.500   0.5563   0.00884   0.00273  -0.0259   0.2981   0.9955
   2.750   0.5826   0.00904   0.00282  -0.0255   0.2896   0.9955
   3.000   0.6092   0.00921   0.00293  -0.0252   0.2828   0.9955
   3.250   0.6356   0.00944   0.00307  -0.0248   0.2765   0.9955
   3.500   0.6624   0.00962   0.00321  -0.0245   0.2717   0.9955
   3.750   0.6892   0.00981   0.00336  -0.0243   0.2668   0.9955
   4.000   0.7157   0.01006   0.00353  -0.0240   0.2623   0.9955
   4.250   0.7422   0.01032   0.00375  -0.0237   0.2584   0.9955
   4.500   0.7694   0.01047   0.00391  -0.0235   0.2558   0.9955
   4.750   0.7965   0.01064   0.00408  -0.0232   0.2529   0.9955
   5.000   0.8234   0.01085   0.00427  -0.0230   0.2497   0.9955
   5.250   0.8499   0.01111   0.00449  -0.0228   0.2465   0.9955
   5.500   0.8759   0.01146   0.00479  -0.0225   0.2431   0.9955
   5.750   0.9032   0.01160   0.00497  -0.0223   0.2413   0.9955
   6.000   0.9302   0.01178   0.00518  -0.0221   0.2390   0.9955
   6.250   0.9571   0.01197   0.00539  -0.0219   0.2364   0.9955
   6.500   0.9838   0.01218   0.00560  -0.0218   0.2336   0.9955
   6.750   1.0099   0.01247   0.00586  -0.0215   0.2305   0.9955
   7.000   1.0356   0.01283   0.00620  -0.0212   0.2272   0.9955
   7.250   1.0626   0.01297   0.00641  -0.0211   0.2249   0.9955
   7.500   1.0891   0.01316   0.00664  -0.0209   0.2221   0.9955
   7.750   1.1155   0.01337   0.00687  -0.0207   0.2192   0.9955
   8.000   1.1413   0.01364   0.00714  -0.0204   0.2161   0.9955
   8.250   1.1659   0.01409   0.00756  -0.0201   0.2123   0.9955
   8.500   1.1925   0.01422   0.00778  -0.0199   0.2098   0.9955
   8.750   1.2187   0.01440   0.00802  -0.0197   0.2062   0.9955
   9.000   1.2443   0.01461   0.00824  -0.0195   0.2021   0.9955
   9.250   1.2684   0.01502   0.00862  -0.0191   0.1974   0.9955
   9.500   1.2948   0.01512   0.00883  -0.0190   0.1935   0.9955
   9.750   1.3203   0.01531   0.00906  -0.0187   0.1887   0.9955
  10.000   1.3440   0.01569   0.00940  -0.0183   0.1835   0.9955
  10.250   1.3700   0.01583   0.00964  -0.0182   0.1781   0.9955
  10.500   1.3941   0.01613   0.00993  -0.0178   0.1725   0.9955
  10.750   1.4180   0.01647   0.01031  -0.0174   0.1673   0.9955
  11.000   1.4416   0.01682   0.01069  -0.0170   0.1620   0.9955
  11.250   1.4636   0.01729   0.01115  -0.0165   0.1569   0.9955
  11.500   1.4863   0.01768   0.01160  -0.0160   0.1521   0.9955
  11.750   1.5069   0.01823   0.01214  -0.0153   0.1468   0.9955
  12.000   1.5277   0.01874   0.01269  -0.0146   0.1424   0.9955
  12.250   1.5476   0.01929   0.01328  -0.0139   0.1384   0.9955
  12.500   1.5651   0.01999   0.01400  -0.0129   0.1349   0.9955
  12.750   1.5829   0.02062   0.01469  -0.0119   0.1318   0.9955
  13.000   1.6009   0.02121   0.01536  -0.0110   0.1287   0.9955
  13.250   1.6157   0.02196   0.01616  -0.0098   0.1254   0.9955
  13.500   1.6243   0.02291   0.01713  -0.0078   0.1224   0.9955
  13.750   1.6365   0.02366   0.01798  -0.0063   0.1197   0.9955
  14.000   1.6478   0.02451   0.01892  -0.0049   0.1169   0.9955
  14.250   1.6554   0.02570   0.02018  -0.0036   0.1142   0.9955
  14.500   1.6587   0.02736   0.02190  -0.0026   0.1115   0.9955
  14.750   1.6649   0.02902   0.02366  -0.0021   0.1091   0.9955
  15.000   1.6725   0.03072   0.02548  -0.0021   0.1063   0.9955
  15.250   1.6748   0.03318   0.02802  -0.0026   0.1033   0.9955
  15.500   1.6702   0.03670   0.03162  -0.0038   0.1005   0.9955
  15.750   1.6701   0.03982   0.03486  -0.0049   0.0981   0.9955
  16.000   1.6677   0.04331   0.03848  -0.0062   0.0954   0.9955
  16.250   1.6579   0.04775   0.04302  -0.0079   0.0927   0.9955
  16.500   1.6415   0.05297   0.04833  -0.0098   0.0906   0.9955
  16.750   1.6280   0.05774   0.05321  -0.0113   0.0885   0.9955
  17.000   1.6139   0.06255   0.05813  -0.0128   0.0857   0.9955
  17.250   1.5937   0.06811   0.06378  -0.0146   0.0833   0.9955
  17.500   1.5704   0.07420   0.06995  -0.0167   0.0811   0.9955
  17.750   1.5535   0.07962   0.07546  -0.0186   0.0787   0.9955
  18.000   1.5353   0.08538   0.08132  -0.0207   0.0756   0.9955
  18.250   1.5123   0.09201   0.08802  -0.0233   0.0728   0.9955
  18.500   1.4934   0.09813   0.09422  -0.0257   0.0698   0.9955
  18.750   1.4715   0.10487   0.10104  -0.0284   0.0661   0.9955
  19.000   1.4483   0.11189   0.10812  -0.0314   0.0627   0.9955
  19.250   1.4264   0.11887   0.11516  -0.0345   0.0588   0.9955
<< Back to TsAGI R-3a (12%) (tsagi-r-3a-il)

Polar data table (+)

Polar graphs


<< Back to TsAGI R-3a (12%) (tsagi-r-3a-il)