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TsAGI R-3a (12%) (tsagi-r-3a-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: TsAGI R-3a (12%) (tsagi-r-3a-il)
Reynolds number: 200,000
Max Cl/Cd: 60.81 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-tsagi-r-3a-il-200000-n5.txt
Download as CSV file: xf-tsagi-r-3a-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4693   0.10107   0.09766   0.0062   1.0045   0.0256
  -9.000  -0.4785   0.08805   0.08468  -0.0011   1.0045   0.0218
  -8.750  -0.4750   0.08436   0.08103  -0.0033   1.0045   0.0217
  -8.500  -0.4741   0.08000   0.07671  -0.0063   1.0045   0.0215
  -8.250  -0.4769   0.07472   0.07148  -0.0110   1.0045   0.0212
  -8.000  -0.4813   0.06765   0.06440  -0.0186   1.0045   0.0209
  -7.750  -0.4854   0.05906   0.05568  -0.0256   1.0045   0.0204
  -7.500  -0.5035   0.04431   0.04034  -0.0319   1.0045   0.0196
  -7.250  -0.5107   0.03352   0.02857  -0.0328   1.0045   0.0193
  -7.000  -0.4876   0.02965   0.02420  -0.0341   0.9675   0.0195
  -6.750  -0.4571   0.02681   0.02087  -0.0357   0.9101   0.0198
  -6.500  -0.4328   0.02485   0.01842  -0.0351   0.8414   0.0201
  -6.250  -0.4121   0.02340   0.01645  -0.0336   0.7726   0.0204
  -6.000  -0.3902   0.02224   0.01478  -0.0322   0.7108   0.0210
  -5.750  -0.3666   0.02109   0.01307  -0.0311   0.6598   0.0218
  -5.500  -0.3419   0.02057   0.01235  -0.0305   0.6196   0.0224
  -5.250  -0.3162   0.01998   0.01154  -0.0300   0.5894   0.0231
  -5.000  -0.2902   0.01926   0.01059  -0.0295   0.5658   0.0236
  -4.250  -0.2112   0.01735   0.00810  -0.0280   0.5114   0.0258
  -4.000  -0.1844   0.01692   0.00758  -0.0277   0.4976   0.0268
  -3.750  -0.1574   0.01648   0.00702  -0.0273   0.4871   0.0283
  -3.500  -0.1304   0.01608   0.00653  -0.0270   0.4778   0.0301
  -3.250  -0.1031   0.01576   0.00613  -0.0267   0.4704   0.0332
  -3.000  -0.0758   0.01539   0.00573  -0.0264   0.4632   0.0368
  -2.500  -0.0211   0.01474   0.00497  -0.0258   0.4506   0.0483
  -2.250   0.0064   0.01450   0.00470  -0.0256   0.4444   0.0570
  -1.750   0.0613   0.01402   0.00436  -0.0252   0.4333   0.0987
  -1.500   0.0887   0.01378   0.00423  -0.0250   0.4276   0.1362
  -1.250   0.1159   0.01358   0.00410  -0.0248   0.4226   0.1771
  -1.000   0.1431   0.01328   0.00399  -0.0246   0.4177   0.2346
  -0.750   0.1692   0.01281   0.00391  -0.0244   0.4123   0.3517
  -0.500   0.1919   0.01207   0.00391  -0.0234   0.4073   0.5619
  -0.250   0.2118   0.01150   0.00399  -0.0211   0.4027   0.7541
   0.000   0.2411   0.01129   0.00409  -0.0202   0.3966   0.8860
   0.250   0.2856   0.01135   0.00408  -0.0230   0.3895   0.9533
   0.500   0.3324   0.01142   0.00404  -0.0265   0.3816   0.9875
   0.750   0.3669   0.01149   0.00400  -0.0278   0.3735   0.9955
   1.000   0.3927   0.01157   0.00398  -0.0273   0.3665   0.9955
   1.250   0.4187   0.01164   0.00398  -0.0268   0.3585   0.9955
   1.500   0.4446   0.01174   0.00397  -0.0263   0.3510   0.9955
   1.750   0.4709   0.01183   0.00400  -0.0259   0.3421   0.9955
   2.000   0.4972   0.01195   0.00403  -0.0254   0.3337   0.9955
   2.250   0.5236   0.01207   0.00407  -0.0250   0.3242   0.9955
   2.500   0.5500   0.01221   0.00413  -0.0247   0.3154   0.9955
   2.750   0.5764   0.01236   0.00420  -0.0243   0.3070   0.9955
   3.000   0.6029   0.01254   0.00430  -0.0239   0.2992   0.9955
   3.250   0.6292   0.01274   0.00440  -0.0236   0.2921   0.9955
   3.500   0.6556   0.01295   0.00455  -0.0233   0.2862   0.9955
   3.750   0.6820   0.01318   0.00472  -0.0229   0.2812   0.9955
   4.000   0.7081   0.01344   0.00490  -0.0226   0.2766   0.9955
   4.250   0.7344   0.01370   0.00511  -0.0223   0.2718   0.9955
   4.500   0.7606   0.01396   0.00534  -0.0220   0.2663   0.9955
   4.750   0.7864   0.01426   0.00556  -0.0217   0.2613   0.9955
   5.000   0.8124   0.01457   0.00582  -0.0214   0.2574   0.9955
   5.250   0.8388   0.01482   0.00611  -0.0211   0.2535   0.9955
   5.500   0.8648   0.01511   0.00639  -0.0208   0.2498   0.9955
   5.750   0.8905   0.01543   0.00668  -0.0205   0.2462   0.9955
   6.000   0.9159   0.01582   0.00701  -0.0201   0.2431   0.9955
   6.250   0.9421   0.01609   0.00734  -0.0199   0.2402   0.9955
   6.500   0.9680   0.01638   0.00767  -0.0196   0.2368   0.9955
   6.750   0.9935   0.01669   0.00800  -0.0193   0.2333   0.9955
   7.000   1.0186   0.01705   0.00835  -0.0189   0.2300   0.9955
   7.250   1.0436   0.01745   0.00873  -0.0186   0.2271   0.9955
   7.500   1.0691   0.01776   0.00913  -0.0183   0.2240   0.9955
   7.750   1.0942   0.01809   0.00954  -0.0180   0.2208   0.9955
   8.000   1.1189   0.01845   0.00994  -0.0176   0.2175   0.9955
   8.250   1.1431   0.01885   0.01034  -0.0172   0.2143   0.9955
   8.500   1.1672   0.01927   0.01079  -0.0168   0.2110   0.9955
   8.750   1.1916   0.01961   0.01126  -0.0164   0.2072   0.9955
   9.000   1.2155   0.01999   0.01173  -0.0160   0.2034   0.9955
   9.250   1.2387   0.02042   0.01218  -0.0155   0.2001   0.9955
   9.500   1.2614   0.02090   0.01268  -0.0150   0.1969   0.9955
   9.750   1.2846   0.02131   0.01325  -0.0145   0.1931   0.9955
  10.000   1.3071   0.02175   0.01379  -0.0140   0.1892   0.9955
  10.250   1.3287   0.02222   0.01430  -0.0133   0.1856   0.9955
  10.500   1.3498   0.02274   0.01489  -0.0127   0.1820   0.9955
  10.750   1.3710   0.02324   0.01554  -0.0120   0.1777   0.9955
  11.000   1.3911   0.02377   0.01614  -0.0113   0.1737   0.9955
  11.250   1.4097   0.02435   0.01675  -0.0104   0.1704   0.9955
  11.500   1.4288   0.02496   0.01751  -0.0096   0.1661   0.9955
  11.750   1.4462   0.02559   0.01823  -0.0087   0.1618   0.9955
  12.000   1.4612   0.02629   0.01896  -0.0076   0.1579   0.9955
  12.250   1.4762   0.02706   0.01985  -0.0065   0.1534   0.9955
  12.500   1.4872   0.02789   0.02077  -0.0049   0.1493   0.9955
  12.750   1.4941   0.02892   0.02183  -0.0031   0.1459   0.9955
  13.000   1.5020   0.03009   0.02311  -0.0018   0.1425   0.9955
  13.250   1.5083   0.03148   0.02462  -0.0007   0.1391   0.9955
  13.500   1.5115   0.03323   0.02645  -0.0001   0.1360   0.9955
  14.000   1.5148   0.03773   0.03115  -0.0001   0.1305   0.9955
  14.250   1.5152   0.04044   0.03400  -0.0008   0.1279   0.9955
  14.500   1.5128   0.04361   0.03729  -0.0018   0.1255   0.9955
  14.750   1.5078   0.04721   0.04098  -0.0031   0.1233   0.9955
  15.000   1.5011   0.05103   0.04485  -0.0045   0.1213   0.9955
  15.250   1.4952   0.05492   0.04893  -0.0059   0.1192   0.9955
  15.500   1.4861   0.05922   0.05338  -0.0075   0.1169   0.9955
  15.750   1.4747   0.06381   0.05809  -0.0092   0.1148   0.9955
  16.000   1.4623   0.06849   0.06286  -0.0109   0.1129   0.9955
  16.250   1.4500   0.07311   0.06753  -0.0126   0.1110   0.9955
  16.500   1.4367   0.07811   0.07266  -0.0145   0.1091   0.9955
  16.750   1.4209   0.08370   0.07841  -0.0167   0.1071   0.9955
  17.000   1.4039   0.08960   0.08445  -0.0192   0.1051   0.9955
  17.250   1.3876   0.09550   0.09046  -0.0217   0.1031   0.9955
  17.500   1.3745   0.10095   0.09598  -0.0241   0.1010   0.9955
  17.750   1.3618   0.10641   0.10151  -0.0264   0.0990   0.9955
  18.000   1.3379   0.11407   0.10936  -0.0300   0.0972   0.9955
  18.250   1.3106   0.12250   0.11795  -0.0341   0.0949   0.9955
  18.500   1.2895   0.12993   0.12549  -0.0377   0.0927   0.9955
  18.750   1.2871   0.13389   0.12946  -0.0397   0.0903   0.9955
  19.000   1.2500   0.14478   0.14052  -0.0455   0.0878   0.9955
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