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TSAGI 8% AIRFOIL (tsagi8-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: TSAGI 8% AIRFOIL (tsagi8-il)
Reynolds number: 100,000
Max Cl/Cd: 45.29 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-tsagi8-il-100000.txt
Download as CSV file: xf-tsagi8-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5619   0.09918   0.09438  -0.0066   1.0000   0.0914
  -8.750  -0.5779   0.09546   0.09075  -0.0127   1.0000   0.0924
  -8.500  -0.5994   0.09231   0.08762  -0.0169   1.0000   0.0928
  -8.250  -0.5655   0.08684   0.08219  -0.0113   1.0000   0.0976
  -8.000  -0.5688   0.08330   0.07868  -0.0124   1.0000   0.1009
  -7.750  -0.4934   0.07001   0.06572  -0.0152   1.0000   0.1133
  -7.500  -0.5068   0.06602   0.06176  -0.0164   1.0000   0.1163
  -7.250  -0.5357   0.06190   0.05749  -0.0200   1.0000   0.1200
  -7.000  -0.5245   0.05668   0.05236  -0.0185   1.0000   0.1237
  -6.750  -0.5772   0.06388   0.05906  -0.0175   1.0000   0.1234
  -6.500  -0.5800   0.06184   0.05663  -0.0175   1.0000   0.1348
  -6.250  -0.5623   0.05710   0.05215  -0.0159   1.0000   0.1394
  -6.000  -0.5551   0.05401   0.04897  -0.0148   1.0000   0.1528
  -5.750  -0.5457   0.05131   0.04620  -0.0132   1.0000   0.1692
  -5.500  -0.5402   0.04872   0.04344  -0.0115   1.0000   0.1919
  -5.250  -0.5285   0.04581   0.04055  -0.0095   1.0000   0.2079
  -5.000  -0.5014   0.03472   0.02744  -0.0074   1.0000   0.0771
  -4.750  -0.4837   0.03135   0.02317  -0.0038   1.0000   0.0659
  -4.500  -0.4656   0.02796   0.01952  -0.0019   1.0000   0.0644
  -4.250  -0.4455   0.02552   0.01668   0.0001   1.0000   0.0643
  -4.000  -0.4252   0.02347   0.01431   0.0019   1.0000   0.0683
  -3.750  -0.4033   0.02176   0.01251   0.0032   1.0000   0.0726
  -3.500  -0.3798   0.02021   0.01073   0.0048   1.0000   0.0771
  -3.250  -0.3585   0.01882   0.00936   0.0062   1.0000   0.0860
  -3.000  -0.3385   0.01762   0.00816   0.0078   1.0000   0.0979
  -2.750  -0.0974   0.01299   0.00641  -0.0289   1.0000   1.0000
  -2.500  -0.0795   0.01278   0.00602  -0.0275   1.0000   1.0000
  -2.250  -0.0620   0.01261   0.00570  -0.0261   1.0000   1.0000
  -2.000  -0.0451   0.01248   0.00545  -0.0245   1.0000   1.0000
  -1.750  -0.0294   0.01239   0.00527  -0.0227   1.0000   1.0000
  -1.500  -0.0154   0.01235   0.00514  -0.0206   1.0000   1.0000
  -1.250  -0.0042   0.01239   0.00513  -0.0181   1.0000   1.0000
  -1.000   0.0012   0.01255   0.00526  -0.0147   1.0000   1.0000
  -0.750  -0.0014   0.01287   0.00555  -0.0102   1.0000   1.0000
  -0.500  -0.0062   0.01331   0.00594  -0.0057   1.0000   1.0000
  -0.250   0.0447   0.01349   0.00605  -0.0114   0.9882   1.0000
   0.000   0.1038   0.01357   0.00606  -0.0184   0.9742   1.0000
   0.250   0.1626   0.01355   0.00602  -0.0251   0.9606   1.0000
   0.500   0.2218   0.01344   0.00592  -0.0317   0.9469   1.0000
   0.750   0.2758   0.01328   0.00579  -0.0370   0.9308   1.0000
   1.000   0.3248   0.01310   0.00565  -0.0411   0.9130   1.0000
   1.250   0.3597   0.01305   0.00565  -0.0423   0.8899   1.0000
   1.500   0.3894   0.01305   0.00566  -0.0422   0.8677   1.0000
   1.750   0.4139   0.01313   0.00574  -0.0411   0.8454   1.0000
   2.000   0.4358   0.01327   0.00589  -0.0395   0.8234   1.0000
   2.250   0.4573   0.01342   0.00608  -0.0377   0.8029   1.0000
   2.500   0.4782   0.01361   0.00630  -0.0359   0.7817   1.0000
   2.750   0.4994   0.01380   0.00651  -0.0342   0.7617   1.0000
   3.000   0.5206   0.01401   0.00676  -0.0324   0.7413   1.0000
   3.250   0.5418   0.01421   0.00701  -0.0307   0.7207   1.0000
   3.500   0.5633   0.01442   0.00732  -0.0289   0.7001   1.0000
   3.750   0.5846   0.01460   0.00758  -0.0272   0.6782   1.0000
   4.000   0.6042   0.01463   0.00761  -0.0246   0.6491   1.0000
   4.250   0.6201   0.01438   0.00727  -0.0209   0.5998   1.0000
   4.500   0.6367   0.01429   0.00710  -0.0177   0.5450   1.0000
   4.750   0.6522   0.01440   0.00708  -0.0146   0.4655   1.0000
   5.000   0.6485   0.01730   0.00789  -0.0093   0.1223   1.0000
   5.250   0.6600   0.01930   0.00955  -0.0065   0.0842   1.0000
   5.500   0.6746   0.02077   0.01098  -0.0041   0.0707   1.0000
   5.750   0.6926   0.02209   0.01237  -0.0019   0.0646   1.0000
   6.000   0.7118   0.02399   0.01413  -0.0002   0.0601   1.0000
   6.250   0.7341   0.02575   0.01603   0.0012   0.0557   1.0000
   6.500   0.7570   0.02758   0.01803   0.0026   0.0527   1.0000
   6.750   0.7800   0.02997   0.02073   0.0041   0.0519   1.0000
   7.000   0.8008   0.03270   0.02388   0.0059   0.0527   1.0000
   7.250   0.8187   0.03589   0.02752   0.0080   0.0546   1.0000
   7.500   0.8337   0.03952   0.03153   0.0101   0.0566   1.0000
   7.750   0.8453   0.04305   0.03545   0.0123   0.0572   1.0000
   8.000   0.8546   0.04702   0.03974   0.0143   0.0579   1.0000
   8.250   0.8585   0.05185   0.04534   0.0178   0.0697   1.0000
  10.500   0.7012   0.11027   0.10521   0.0018   0.1497   1.0000
  10.750   0.7209   0.11310   0.10811   0.0055   0.1372   1.0000
  11.000   0.6891   0.11866   0.11353  -0.0021   0.1353   1.0000
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