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SD6080 (9.2%) (sd6080-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: SD6080 (9.2%) (sd6080-il)
Reynolds number: 100,000
Max Cl/Cd: 60.46 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd6080-il-100000-n5.txt
Download as CSV file: xf-sd6080-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD6080 (9.2%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3487   0.09200   0.08748  -0.0407   1.0000   0.0495
  -7.750  -0.3525   0.08905   0.08463  -0.0420   1.0000   0.0495
  -7.500  -0.3572   0.08629   0.08197  -0.0426   1.0000   0.0495
  -7.250  -0.3633   0.07877   0.07451  -0.0400   1.0000   0.0296
  -7.000  -0.3520   0.07661   0.07234  -0.0386   0.9951   0.0281
  -6.750  -0.3294   0.07128   0.06698  -0.0462   0.9844   0.0266
  -6.500  -0.3038   0.06469   0.06032  -0.0562   0.9735   0.0256
  -6.250  -0.2774   0.05801   0.05349  -0.0656   0.9625   0.0256
  -6.000  -0.2510   0.05134   0.04660  -0.0734   0.9519   0.0253
  -5.750  -0.2235   0.04495   0.03986  -0.0798   0.9426   0.0252
  -5.500  -0.1982   0.03863   0.03301  -0.0841   0.9323   0.0243
  -5.250  -0.1735   0.03278   0.02632  -0.0865   0.9221   0.0234
  -5.000  -0.1449   0.02935   0.02229  -0.0879   0.9147   0.0234
  -4.750  -0.1195   0.02687   0.01934  -0.0881   0.9051   0.0236
  -4.500  -0.0918   0.02479   0.01685  -0.0884   0.8973   0.0241
  -4.250  -0.0641   0.02309   0.01481  -0.0884   0.8890   0.0248
  -4.000  -0.0367   0.02168   0.01313  -0.0882   0.8808   0.0261
  -3.750  -0.0085   0.02060   0.01175  -0.0880   0.8732   0.0290
  -3.500   0.0174   0.01953   0.01059  -0.0877   0.8646   0.0317
  -3.250   0.0449   0.01858   0.00952  -0.0873   0.8574   0.0346
  -3.000   0.0705   0.01775   0.00854  -0.0867   0.8484   0.0390
  -2.750   0.0979   0.01699   0.00774  -0.0863   0.8417   0.0515
  -2.500   0.1232   0.01628   0.00713  -0.0859   0.8325   0.0850
  -2.250   0.1496   0.01558   0.00673  -0.0857   0.8257   0.1582
  -2.000   0.1748   0.01501   0.00646  -0.0853   0.8168   0.2478
  -1.750   0.2004   0.01442   0.00622  -0.0849   0.8097   0.3746
  -1.500   0.2235   0.01380   0.00614  -0.0838   0.8013   0.5450
  -1.250   0.2431   0.01313   0.00608  -0.0810   0.7942   0.7514
  -1.000   0.2934   0.01268   0.00570  -0.0846   0.7871   1.0000
  -0.750   0.3197   0.01274   0.00553  -0.0841   0.7796   1.0000
  -0.500   0.3458   0.01283   0.00542  -0.0837   0.7711   1.0000
  -0.250   0.3721   0.01293   0.00533  -0.0833   0.7632   1.0000
   0.000   0.3985   0.01302   0.00525  -0.0829   0.7553   1.0000
   0.250   0.4247   0.01314   0.00522  -0.0825   0.7470   1.0000
   0.500   0.4515   0.01323   0.00517  -0.0821   0.7395   1.0000
   0.750   0.4776   0.01337   0.00521  -0.0817   0.7307   1.0000
   1.000   0.5046   0.01345   0.00517  -0.0813   0.7236   1.0000
   1.250   0.5306   0.01361   0.00527  -0.0810   0.7143   1.0000
   1.500   0.5573   0.01372   0.00528  -0.0806   0.7066   1.0000
   1.750   0.5836   0.01386   0.00538  -0.0802   0.6974   1.0000
   2.000   0.6099   0.01401   0.00547  -0.0799   0.6885   1.0000
   2.250   0.6367   0.01412   0.00551  -0.0795   0.6800   1.0000
   2.500   0.6625   0.01428   0.00568  -0.0791   0.6696   1.0000
   2.750   0.6889   0.01442   0.00579  -0.0786   0.6599   1.0000
   3.000   0.7154   0.01454   0.00587  -0.0782   0.6505   1.0000
   3.250   0.7411   0.01471   0.00605  -0.0777   0.6391   1.0000
   3.500   0.7670   0.01486   0.00624  -0.0773   0.6279   1.0000
   3.750   0.7930   0.01501   0.00639  -0.0768   0.6167   1.0000
   4.000   0.8190   0.01515   0.00652  -0.0763   0.6050   1.0000
   4.250   0.8446   0.01531   0.00674  -0.0757   0.5921   1.0000
   4.500   0.8698   0.01549   0.00695  -0.0752   0.5781   1.0000
   4.750   0.8950   0.01568   0.00717  -0.0746   0.5636   1.0000
   5.000   0.9200   0.01587   0.00740  -0.0740   0.5484   1.0000
   5.250   0.9447   0.01608   0.00768  -0.0733   0.5319   1.0000
   5.500   0.9690   0.01631   0.00798  -0.0726   0.5136   1.0000
   5.750   0.9929   0.01657   0.00827  -0.0718   0.4941   1.0000
   6.000   1.0164   0.01685   0.00858  -0.0710   0.4731   1.0000
   6.250   1.0393   0.01719   0.00897  -0.0701   0.4495   1.0000
   6.500   1.0615   0.01758   0.00937  -0.0692   0.4239   1.0000
   6.750   1.0828   0.01804   0.00982  -0.0681   0.3961   1.0000
   7.000   1.1031   0.01859   0.01033  -0.0670   0.3666   1.0000
   7.250   1.1224   0.01923   0.01094  -0.0657   0.3360   1.0000
   7.500   1.1405   0.01997   0.01161  -0.0644   0.3053   1.0000
   7.750   1.1575   0.02079   0.01237  -0.0630   0.2756   1.0000
   8.000   1.1738   0.02168   0.01320  -0.0615   0.2473   1.0000
   8.250   1.1890   0.02264   0.01411  -0.0600   0.2198   1.0000
   8.500   1.2025   0.02369   0.01511  -0.0584   0.1917   1.0000
   8.750   1.2141   0.02486   0.01616  -0.0566   0.1625   1.0000
   9.000   1.2243   0.02611   0.01727  -0.0548   0.1326   1.0000
   9.250   1.2334   0.02741   0.01844  -0.0528   0.1062   1.0000
   9.500   1.2404   0.02873   0.01969  -0.0506   0.0849   1.0000
   9.750   1.2469   0.03015   0.02110  -0.0484   0.0684   1.0000
  10.000   1.2511   0.03181   0.02278  -0.0462   0.0537   1.0000
  10.250   1.2531   0.03374   0.02471  -0.0440   0.0432   1.0000
  10.500   1.2539   0.03584   0.02684  -0.0420   0.0374   1.0000
  10.750   1.2552   0.03799   0.02910  -0.0403   0.0330   1.0000
  11.000   1.2541   0.04043   0.03159  -0.0387   0.0304   1.0000
  11.250   1.2559   0.04272   0.03407  -0.0375   0.0279   1.0000
  11.500   1.2571   0.04513   0.03663  -0.0365   0.0260   1.0000
  11.750   1.2565   0.04783   0.03946  -0.0358   0.0249   1.0000
  12.000   1.2543   0.05082   0.04257  -0.0351   0.0240   1.0000
  12.250   1.2522   0.05391   0.04577  -0.0346   0.0234   1.0000
  12.500   1.2528   0.05682   0.04891  -0.0342   0.0227   1.0000
  12.750   1.2535   0.05984   0.05211  -0.0339   0.0222   1.0000
  13.000   1.2540   0.06297   0.05543  -0.0336   0.0216   1.0000
  13.250   1.2543   0.06623   0.05888  -0.0335   0.0211   1.0000
  13.500   1.2544   0.06960   0.06243  -0.0336   0.0207   1.0000
  13.750   1.2531   0.07323   0.06625  -0.0338   0.0203   1.0000
  14.000   1.2504   0.07712   0.07032  -0.0345   0.0198   1.0000
  14.250   1.2464   0.08130   0.07468  -0.0355   0.0194   1.0000
  14.500   1.2412   0.08574   0.07928  -0.0368   0.0190   1.0000
  14.750   1.2355   0.09045   0.08415  -0.0384   0.0187   1.0000
  15.000   1.2290   0.09537   0.08923  -0.0402   0.0184   1.0000
  15.250   1.2215   0.10066   0.09466  -0.0423   0.0181   1.0000
  15.500   1.2107   0.10684   0.10103  -0.0453   0.0179   1.0000
  15.750   1.1984   0.11362   0.10805  -0.0489   0.0179   1.0000
  16.000   1.1842   0.12116   0.11581  -0.0532   0.0178   1.0000
  16.250   1.1703   0.12896   0.12380  -0.0579   0.0179   1.0000
  16.500   1.1550   0.13754   0.13258  -0.0633   0.0179   1.0000
  16.750   1.1401   0.14649   0.14168  -0.0690   0.0180   1.0000
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