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TSAGI 12% AIRFOIL (tsagi12-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: TSAGI 12% AIRFOIL (tsagi12-il)
Reynolds number: 50,000
Max Cl/Cd: 32.27 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-tsagi12-il-50000-n5.txt
Download as CSV file: xf-tsagi12-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: TSAGI 12% AIRFOIL                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5015   0.10109   0.09403  -0.0311   1.0000   0.0546
 -10.500  -0.5065   0.09578   0.08879  -0.0336   1.0000   0.0544
 -10.250  -0.5139   0.09001   0.08307  -0.0368   1.0000   0.0541
 -10.000  -0.5235   0.08403   0.07714  -0.0406   1.0000   0.0537
  -9.750  -0.5391   0.07846   0.07160  -0.0432   1.0000   0.0534
  -9.500  -0.5574   0.07383   0.06696  -0.0439   1.0000   0.0531
  -9.250  -0.5775   0.06994   0.06304  -0.0426   1.0000   0.0528
  -9.000  -0.5968   0.06627   0.05929  -0.0402   1.0000   0.0528
  -8.750  -0.6141   0.06249   0.05535  -0.0376   1.0000   0.0530
  -8.500  -0.6279   0.05884   0.05148  -0.0344   1.0000   0.0535
  -8.250  -0.6398   0.05530   0.04762  -0.0308   1.0000   0.0543
  -8.000  -0.6499   0.05191   0.04379  -0.0267   1.0000   0.0552
  -7.750  -0.6449   0.04974   0.04165  -0.0242   1.0000   0.0572
  -7.500  -0.6406   0.04761   0.03939  -0.0213   1.0000   0.0591
  -7.250  -0.6386   0.04505   0.03653  -0.0179   1.0000   0.0605
  -7.000  -0.6356   0.04261   0.03371  -0.0143   1.0000   0.0627
  -6.750  -0.6325   0.04034   0.03095  -0.0105   1.0000   0.0659
  -6.500  -0.6262   0.03829   0.02859  -0.0072   1.0000   0.0691
  -6.250  -0.6162   0.03666   0.02684  -0.0046   1.0000   0.0720
  -6.000  -0.6057   0.03506   0.02499  -0.0019   1.0000   0.0757
  -5.750  -0.5953   0.03365   0.02307   0.0011   1.0000   0.0809
  -5.500  -0.5818   0.03224   0.02170   0.0031   1.0000   0.0854
  -5.250  -0.5660   0.03094   0.02021   0.0050   1.0000   0.0898
  -5.000  -0.5379   0.02959   0.01861   0.0045   0.9960   0.0976
  -4.750  -0.4970   0.02833   0.01715   0.0018   0.9877   0.1093
  -4.500  -0.4547   0.02712   0.01584  -0.0012   0.9797   0.1217
  -4.250  -0.4131   0.02617   0.01492  -0.0043   0.9710   0.1421
  -4.000  -0.3710   0.02527   0.01399  -0.0075   0.9623   0.1703
  -3.750  -0.3338   0.02432   0.01320  -0.0099   0.9516   0.2127
  -3.500  -0.2989   0.02312   0.01240  -0.0120   0.9409   0.2802
  -3.250  -0.2705   0.02154   0.01175  -0.0127   0.9303   0.4374
  -3.000  -0.1532   0.02157   0.01296  -0.0248   0.9379   0.8543
  -2.750  -0.0748   0.02253   0.01351  -0.0322   0.9346   0.9354
  -2.500   0.0134   0.02254   0.01308  -0.0434   0.9309   0.9739
  -2.250   0.0988   0.02185   0.01204  -0.0552   0.9249   1.0000
  -2.000   0.1380   0.02157   0.01154  -0.0582   0.9084   1.0000
  -1.750   0.1745   0.02133   0.01109  -0.0605   0.8919   1.0000
  -1.500   0.2081   0.02114   0.01072  -0.0620   0.8754   1.0000
  -1.250   0.2386   0.02100   0.01041  -0.0629   0.8593   1.0000
  -1.000   0.2653   0.02093   0.01019  -0.0630   0.8429   1.0000
  -0.750   0.2898   0.02091   0.01005  -0.0626   0.8267   1.0000
  -0.500   0.3130   0.02093   0.00994  -0.0619   0.8112   1.0000
  -0.250   0.3354   0.02097   0.00988  -0.0610   0.7962   1.0000
   0.000   0.3573   0.02103   0.00985  -0.0600   0.7819   1.0000
   0.250   0.3791   0.02110   0.00984  -0.0589   0.7680   1.0000
   0.500   0.4002   0.02120   0.00987  -0.0577   0.7541   1.0000
   0.750   0.4207   0.02134   0.00996  -0.0564   0.7404   1.0000
   1.000   0.4411   0.02149   0.01007  -0.0551   0.7269   1.0000
   1.250   0.4616   0.02165   0.01021  -0.0538   0.7137   1.0000
   1.500   0.4826   0.02182   0.01036  -0.0527   0.7013   1.0000
   1.750   0.5045   0.02198   0.01051  -0.0516   0.6894   1.0000
   2.000   0.5270   0.02212   0.01063  -0.0505   0.6782   1.0000
   2.250   0.5474   0.02238   0.01092  -0.0493   0.6657   1.0000
   2.500   0.5679   0.02264   0.01121  -0.0481   0.6537   1.0000
   2.750   0.5890   0.02290   0.01150  -0.0469   0.6427   1.0000
   3.000   0.6115   0.02309   0.01171  -0.0458   0.6329   1.0000
   3.250   0.6308   0.02346   0.01215  -0.0445   0.6211   1.0000
   3.500   0.6506   0.02382   0.01258  -0.0432   0.6102   1.0000
   3.750   0.6721   0.02410   0.01292  -0.0420   0.6005   1.0000
   4.000   0.6919   0.02446   0.01337  -0.0406   0.5900   1.0000
   4.250   0.7106   0.02491   0.01393  -0.0392   0.5792   1.0000
   4.500   0.7313   0.02523   0.01436  -0.0378   0.5697   1.0000
   4.750   0.7511   0.02561   0.01484  -0.0364   0.5596   1.0000
   5.000   0.7688   0.02612   0.01549  -0.0348   0.5489   1.0000
   5.250   0.7887   0.02649   0.01597  -0.0333   0.5391   1.0000
   5.500   0.8088   0.02684   0.01648  -0.0319   0.5293   1.0000
   5.750   0.8254   0.02739   0.01720  -0.0301   0.5181   1.0000
   6.000   0.8438   0.02783   0.01779  -0.0284   0.5077   1.0000
   6.250   0.8658   0.02805   0.01812  -0.0270   0.4979   1.0000
   6.500   0.8815   0.02861   0.01888  -0.0250   0.4860   1.0000
   6.750   0.8978   0.02913   0.01963  -0.0230   0.4741   1.0000
   7.000   0.9151   0.02951   0.02018  -0.0210   0.4613   1.0000
   7.250   0.9318   0.02971   0.02053  -0.0187   0.4456   1.0000
   7.500   0.9480   0.02981   0.02075  -0.0162   0.4279   1.0000
   7.750   0.9641   0.02988   0.02092  -0.0137   0.4094   1.0000
   8.000   0.9711   0.03026   0.02147  -0.0101   0.3868   1.0000
   8.250   0.9747   0.03046   0.02177  -0.0059   0.3577   1.0000
   8.500   0.9731   0.03087   0.02217  -0.0012   0.3229   1.0000
   8.750   0.9696   0.03159   0.02285   0.0034   0.2855   1.0000
   9.000   0.9636   0.03263   0.02370   0.0080   0.2443   1.0000
   9.250   0.9515   0.03402   0.02482   0.0132   0.2054   1.0000
   9.500   0.9367   0.03592   0.02644   0.0178   0.1692   1.0000
   9.750   0.9214   0.03836   0.02862   0.0214   0.1395   1.0000
  10.000   0.9075   0.04116   0.03121   0.0240   0.1184   1.0000
  10.250   0.8952   0.04419   0.03409   0.0260   0.1024   1.0000
  10.500   0.8846   0.04732   0.03709   0.0274   0.0913   1.0000
  10.750   0.8764   0.05041   0.04012   0.0286   0.0827   1.0000
  11.000   0.8716   0.05331   0.04304   0.0297   0.0753   1.0000
  11.250   0.8677   0.05619   0.04590   0.0306   0.0696   1.0000
  11.500   0.8675   0.05880   0.04859   0.0315   0.0640   1.0000
  11.750   0.8678   0.06142   0.05126   0.0323   0.0590   1.0000
  12.000   0.8693   0.06386   0.05366   0.0331   0.0560   1.0000
  12.250   0.8777   0.06588   0.05596   0.0345   0.0528   1.0000
  12.500   0.8840   0.06816   0.05841   0.0354   0.0498   1.0000
  12.750   0.8880   0.07065   0.06096   0.0360   0.0469   1.0000
  13.000   0.8956   0.07286   0.06315   0.0370   0.0448   1.0000
  13.250   0.8984   0.07609   0.06673   0.0373   0.0431   1.0000
  13.500   0.8994   0.07961   0.07053   0.0374   0.0422   1.0000
  13.750   0.8947   0.08387   0.07505   0.0368   0.0414   1.0000
  14.000   0.8864   0.08861   0.08003   0.0356   0.0409   1.0000
  14.250   0.8745   0.09407   0.08571   0.0337   0.0408   1.0000
  14.500   0.8587   0.10041   0.09226   0.0310   0.0407   1.0000
  14.750   0.8401   0.10770   0.09974   0.0275   0.0410   1.0000
  15.000   0.8181   0.11628   0.10849   0.0231   0.0414   1.0000
  15.250   0.7944   0.12603   0.11836   0.0179   0.0421   1.0000
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