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NASA SC(2)-0406 AIRFOIL (sc20406-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0406 AIRFOIL (sc20406-il)
Reynolds number: 200,000
Max Cl/Cd: 47.55 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20406-il-200000.txt
Download as CSV file: xf-sc20406-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0406 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6687   0.09117   0.08771   0.0044   1.0000   0.0430
  -8.500  -0.6722   0.08464   0.08124  -0.0045   1.0000   0.0438
  -8.250  -0.6721   0.07732   0.07374  -0.0162   1.0000   0.0445
  -8.000  -0.6683   0.07254   0.06870  -0.0209   1.0000   0.0449
  -7.750  -0.6640   0.06670   0.06263  -0.0241   1.0000   0.0452
  -7.500  -0.6584   0.05942   0.05549  -0.0250   1.0000   0.0468
  -7.250  -0.6449   0.05599   0.05204  -0.0255   1.0000   0.0484
  -7.000  -0.6295   0.05257   0.04850  -0.0267   1.0000   0.0519
  -6.750  -0.6116   0.04699   0.04220  -0.0304   1.0000   0.0590
  -6.500  -0.5935   0.04358   0.03891  -0.0307   1.0000   0.0617
  -6.250  -0.5715   0.04032   0.03542  -0.0316   1.0000   0.0657
  -6.000  -0.5239   0.02179   0.01685  -0.0324   1.0000   0.0740
  -5.750  -0.5024   0.01895   0.01383  -0.0327   1.0000   0.0772
  -5.500  -0.4828   0.02282   0.01555  -0.0324   1.0000   0.0318
  -5.250  -0.4548   0.02036   0.01270  -0.0323   1.0000   0.0321
  -5.000  -0.4268   0.01881   0.01086  -0.0321   1.0000   0.0330
  -4.750  -0.4006   0.01652   0.00853  -0.0322   1.0000   0.0382
  -4.500  -0.3730   0.01529   0.00720  -0.0319   1.0000   0.0428
  -4.250  -0.3454   0.01375   0.00568  -0.0319   1.0000   0.0527
  -4.000  -0.3174   0.01295   0.00481  -0.0321   1.0000   0.0715
  -3.750  -0.2894   0.01212   0.00410  -0.0325   1.0000   0.0951
  -3.500  -0.2603   0.01115   0.00332  -0.0332   1.0000   0.1330
  -3.250  -0.2306   0.00870   0.00282  -0.0353   1.0000   0.5682
  -3.000  -0.2061   0.00845   0.00287  -0.0341   1.0000   0.6806
  -2.750  -0.1816   0.00839   0.00288  -0.0329   1.0000   0.7275
  -2.500  -0.1576   0.00837   0.00290  -0.0317   1.0000   0.7632
  -2.250  -0.1343   0.00837   0.00292  -0.0302   1.0000   0.7934
  -2.000  -0.1127   0.00836   0.00295  -0.0283   1.0000   0.8187
  -1.750  -0.0932   0.00836   0.00298  -0.0259   1.0000   0.8442
  -1.500  -0.0775   0.00835   0.00304  -0.0225   1.0000   0.8732
  -1.250  -0.0641   0.00826   0.00301  -0.0187   1.0000   0.8994
  -1.000  -0.0479   0.00811   0.00289  -0.0158   1.0000   0.9209
  -0.750  -0.0301   0.00792   0.00272  -0.0135   1.0000   0.9417
  -0.500  -0.0073   0.00772   0.00254  -0.0124   1.0000   0.9648
  -0.250   0.0227   0.00758   0.00243  -0.0133   1.0000   0.9994
   0.000   0.0545   0.00761   0.00246  -0.0150   1.0000   1.0000
   0.250   0.0864   0.00767   0.00253  -0.0166   1.0000   1.0000
   0.500   0.1180   0.00776   0.00265  -0.0181   1.0000   1.0000
   0.750   0.1489   0.00787   0.00281  -0.0194   1.0000   1.0000
   1.000   0.1793   0.00801   0.00300  -0.0205   1.0000   1.0000
   1.250   0.2134   0.00813   0.00321  -0.0224   0.9973   1.0000
   1.500   0.2797   0.00789   0.00317  -0.0300   0.9714   1.0000
   1.750   0.3296   0.00766   0.00305  -0.0337   0.9262   1.0000
   2.000   0.3623   0.00762   0.00298  -0.0334   0.8460   1.0000
   2.250   0.3795   0.00847   0.00289  -0.0296   0.5911   1.0000
   2.500   0.3963   0.01132   0.00354  -0.0287   0.1375   1.0000
   2.750   0.4236   0.01237   0.00434  -0.0288   0.0950   1.0000
   3.000   0.4517   0.01304   0.00494  -0.0291   0.0710   1.0000
   3.250   0.4788   0.01409   0.00594  -0.0291   0.0515   1.0000
   3.500   0.5052   0.01576   0.00759  -0.0287   0.0409   1.0000
   3.750   0.5335   0.01702   0.00900  -0.0284   0.0375   1.0000
   4.000   0.5617   0.01874   0.01089  -0.0280   0.0357   1.0000
   4.250   0.5897   0.02028   0.01261  -0.0278   0.0333   1.0000
   4.500   0.6158   0.02273   0.01522  -0.0278   0.0304   1.0000
   4.750   0.6428   0.02536   0.01824  -0.0273   0.0306   1.0000
   5.000   0.6699   0.03099   0.02491  -0.0254   0.0378   1.0000
   5.250   0.6967   0.04002   0.03457  -0.0235   0.0683   1.0000
   5.500   0.7176   0.04322   0.03856  -0.0230   0.0595   1.0000
   5.750   0.7371   0.04647   0.04195  -0.0230   0.0569   1.0000
   6.000   0.7546   0.05041   0.04587  -0.0231   0.0552   1.0000
   6.250   0.7629   0.05835   0.05399  -0.0239   0.0537   1.0000
   6.500   0.7815   0.06109   0.05751  -0.0250   0.0481   1.0000
   6.750   0.7932   0.06545   0.06203  -0.0261   0.0456   1.0000
   7.000   0.8045   0.06830   0.06488  -0.0258   0.0433   1.0000
   7.250   0.8041   0.07651   0.07289  -0.0259   0.0413   1.0000
   7.500   0.8075   0.08124   0.07784  -0.0274   0.0412   1.0000
   7.750   0.8094   0.08610   0.08291  -0.0300   0.0410   1.0000
   8.000   0.8077   0.09185   0.08882  -0.0356   0.0405   1.0000
   8.250   0.8024   0.09805   0.09506  -0.0431   0.0402   1.0000
   8.500   0.7984   0.10418   0.10116  -0.0506   0.0395   1.0000
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