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TSAGI 8% AIRFOIL (tsagi8-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: TSAGI 8% AIRFOIL (tsagi8-il)
Reynolds number: 1,000,000
Max Cl/Cd: 76.8 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-tsagi8-il-1000000.txt
Download as CSV file: xf-tsagi8-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: TSAGI 8% AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5855   0.08371   0.08216  -0.0104   1.0000   0.0089
  -9.000  -0.5887   0.07929   0.07776  -0.0136   1.0000   0.0091
  -8.750  -0.6050   0.07222   0.07071  -0.0203   1.0000   0.0089
  -8.500  -0.6171   0.06781   0.06626  -0.0212   1.0000   0.0090
  -8.250  -0.6237   0.06251   0.06090  -0.0225   1.0000   0.0090
  -8.000  -0.6263   0.05784   0.05614  -0.0228   1.0000   0.0090
  -7.750  -0.6271   0.05314   0.05132  -0.0224   1.0000   0.0091
  -7.500  -0.6254   0.04873   0.04677  -0.0214   1.0000   0.0092
  -7.250  -0.6218   0.04458   0.04246  -0.0198   1.0000   0.0094
  -7.000  -0.6357   0.03416   0.03156  -0.0145   1.0000   0.0076
  -6.750  -0.6604   0.02284   0.01927  -0.0059   1.0000   0.0069
  -6.500  -0.6504   0.01990   0.01593  -0.0025   1.0000   0.0074
  -6.250  -0.6345   0.01836   0.01415  -0.0001   1.0000   0.0078
  -6.000  -0.6179   0.01701   0.01259   0.0021   1.0000   0.0080
  -5.750  -0.6001   0.01606   0.01148   0.0041   1.0000   0.0082
  -5.500  -0.5713   0.01410   0.00920   0.0038   0.9981   0.0084
  -5.250  -0.5409   0.01202   0.00688   0.0029   0.9950   0.0093
  -5.000  -0.5080   0.01140   0.00621   0.0017   0.9912   0.0101
  -4.750  -0.4743   0.01083   0.00558   0.0004   0.9866   0.0112
  -4.500  -0.4393   0.01025   0.00494  -0.0013   0.9828   0.0121
  -4.250  -0.4075   0.00983   0.00446  -0.0021   0.9751   0.0127
  -4.000  -0.3731   0.00884   0.00334  -0.0036   0.9686   0.0149
  -3.750  -0.3382   0.00856   0.00306  -0.0052   0.9572   0.0177
  -3.500  -0.3028   0.00840   0.00288  -0.0069   0.9422   0.0196
  -3.250  -0.2746   0.00790   0.00227  -0.0069   0.9195   0.0264
  -3.000  -0.2480   0.00775   0.00202  -0.0065   0.8948   0.0315
  -2.750  -0.2234   0.00758   0.00179  -0.0057   0.8705   0.0401
  -2.500  -0.1991   0.00739   0.00160  -0.0048   0.8478   0.0599
  -2.250  -0.1754   0.00716   0.00144  -0.0040   0.8266   0.1024
  -2.000  -0.1523   0.00686   0.00129  -0.0031   0.8067   0.1670
  -1.750  -0.1303   0.00646   0.00117  -0.0020   0.7881   0.2689
  -1.500  -0.1094   0.00596   0.00104  -0.0007   0.7706   0.3970
  -1.250  -0.0914   0.00533   0.00092   0.0012   0.7538   0.5649
  -1.000  -0.0787   0.00463   0.00082   0.0045   0.7381   0.7532
  -0.750  -0.0584   0.00427   0.00087   0.0065   0.7232   0.8871
  -0.500  -0.0235   0.00430   0.00092   0.0051   0.7082   0.9199
  -0.250   0.0131   0.00441   0.00098   0.0033   0.6935   0.9368
   0.000   0.0495   0.00457   0.00107   0.0015   0.6791   0.9521
   0.250   0.0837   0.00472   0.00115   0.0003   0.6647   0.9591
   0.500   0.1251   0.00497   0.00133  -0.0026   0.6500   0.9659
   0.750   0.1643   0.00520   0.00149  -0.0049   0.6358   0.9716
   1.000   0.2071   0.00538   0.00161  -0.0082   0.6207   0.9743
   1.500   0.2765   0.00573   0.00184  -0.0112   0.5897   0.9830
   1.750   0.3131   0.00579   0.00186  -0.0132   0.5721   0.9840
   2.000   0.3475   0.00587   0.00186  -0.0148   0.5507   0.9853
   2.250   0.3804   0.00592   0.00188  -0.0160   0.5330   0.9866
   2.500   0.4125   0.00601   0.00191  -0.0170   0.5105   0.9881
   2.750   0.4429   0.00621   0.00193  -0.0178   0.4612   0.9899
   3.000   0.4730   0.00640   0.00199  -0.0185   0.4250   0.9918
   3.250   0.5020   0.00664   0.00208  -0.0190   0.3807   0.9936
   3.500   0.5322   0.00693   0.00218  -0.0198   0.3254   0.9950
   3.750   0.5621   0.00742   0.00232  -0.0207   0.2385   0.9963
   4.000   0.5892   0.00836   0.00266  -0.0214   0.1021   0.9978
   4.250   0.6176   0.00915   0.00307  -0.0220   0.0247   0.9992
   4.500   0.6468   0.00944   0.00337  -0.0225   0.0184   1.0000
   4.750   0.6686   0.00984   0.00386  -0.0213   0.0155   1.0000
   5.000   0.6912   0.01008   0.00413  -0.0203   0.0140   1.0000
   5.250   0.7135   0.01034   0.00441  -0.0194   0.0125   1.0000
   5.500   0.7342   0.01085   0.00498  -0.0180   0.0112   1.0000
   5.750   0.7497   0.01207   0.00638  -0.0157   0.0101   1.0000
   6.000   0.7716   0.01234   0.00670  -0.0146   0.0098   1.0000
   6.250   0.7925   0.01274   0.00715  -0.0134   0.0092   1.0000
   6.500   0.8114   0.01342   0.00791  -0.0118   0.0087   1.0000
   6.750   0.8304   0.01408   0.00863  -0.0102   0.0080   1.0000
   7.000   0.8492   0.01475   0.00936  -0.0086   0.0076   1.0000
   7.250   0.8675   0.01551   0.01018  -0.0069   0.0073   1.0000
   7.500   0.8855   0.01626   0.01097  -0.0054   0.0068   1.0000
   7.750   0.8980   0.01815   0.01303  -0.0028   0.0065   1.0000
   8.000   0.9080   0.02116   0.01631   0.0001   0.0063   1.0000
   8.250   0.9216   0.02300   0.01837   0.0023   0.0062   1.0000
   8.500   0.9358   0.02444   0.02002   0.0045   0.0062   1.0000
   8.750   0.9520   0.02527   0.02099   0.0063   0.0060   1.0000
   9.000   0.9654   0.02664   0.02254   0.0084   0.0057   1.0000
   9.250   0.9702   0.02951   0.02573   0.0116   0.0055   1.0000
   9.500   0.9677   0.03322   0.02980   0.0156   0.0054   1.0000
   9.750   0.9566   0.03769   0.03464   0.0200   0.0055   1.0000
  10.000   0.9340   0.04284   0.04014   0.0249   0.0056   1.0000
  10.250   0.9127   0.04584   0.04331   0.0296   0.0058   1.0000
  10.500   0.8897   0.04914   0.04678   0.0327   0.0058   1.0000
  10.750   0.8613   0.05405   0.05186   0.0326   0.0059   1.0000
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