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SD2083 (9.0%) (sd2083-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SD2083 (9.0%) (sd2083-il)
Reynolds number: 50,000
Max Cl/Cd: 38.33 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd2083-il-50000-n5.txt
Download as CSV file: xf-sd2083-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD2083 (9.0%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4033   0.10188   0.09516  -0.0344   1.0000   0.1172
  -8.500  -0.3987   0.09336   0.08661  -0.0384   1.0000   0.0615
  -8.250  -0.4000   0.09011   0.08344  -0.0389   1.0000   0.0608
  -8.000  -0.4042   0.08705   0.08049  -0.0390   1.0000   0.0600
  -7.750  -0.4117   0.08418   0.07773  -0.0390   1.0000   0.0590
  -7.500  -0.4187   0.08103   0.07468  -0.0394   1.0000   0.0579
  -7.250  -0.4268   0.07778   0.07151  -0.0397   1.0000   0.0569
  -6.750  -0.4546   0.06808   0.06150  -0.0441   1.0000   0.0501
  -6.500  -0.4553   0.06482   0.05817  -0.0431   1.0000   0.0499
  -6.250  -0.4541   0.06154   0.05478  -0.0421   1.0000   0.0497
  -6.000  -0.4506   0.05822   0.05135  -0.0411   1.0000   0.0494
  -5.750  -0.4452   0.05489   0.04787  -0.0402   1.0000   0.0490
  -5.500  -0.4377   0.05158   0.04433  -0.0395   1.0000   0.0485
  -5.250  -0.4277   0.04822   0.04063  -0.0389   1.0000   0.0480
  -5.000  -0.4153   0.04495   0.03701  -0.0383   1.0000   0.0477
  -4.750  -0.4005   0.04188   0.03353  -0.0377   1.0000   0.0475
  -4.500  -0.3835   0.03904   0.03025  -0.0370   1.0000   0.0474
  -4.250  -0.3593   0.03623   0.02691  -0.0373   0.9980   0.0476
  -4.000  -0.3271   0.03362   0.02371  -0.0387   0.9935   0.0480
  -3.750  -0.2952   0.03143   0.02097  -0.0397   0.9888   0.0489
  -3.500  -0.2625   0.02964   0.01881  -0.0408   0.9844   0.0512
  -3.250  -0.2316   0.02845   0.01749  -0.0420   0.9795   0.0571
  -3.000  -0.1994   0.02728   0.01593  -0.0426   0.9745   0.0619
  -2.750  -0.1651   0.02610   0.01460  -0.0438   0.9703   0.0670
  -2.500  -0.1344   0.02522   0.01348  -0.0443   0.9648   0.0762
  -2.250  -0.1015   0.02429   0.01256  -0.0456   0.9596   0.1009
  -2.000  -0.0683   0.02264   0.01196  -0.0477   0.9556   0.2578
  -1.500   0.0133   0.02036   0.01153  -0.0513   0.9479   1.0000
  -1.250   0.0497   0.02065   0.01137  -0.0534   0.9421   1.0000
  -1.000   0.0773   0.02088   0.01125  -0.0538   0.9338   1.0000
  -0.750   0.1126   0.02118   0.01123  -0.0556   0.9275   1.0000
  -0.500   0.1408   0.02145   0.01125  -0.0561   0.9191   1.0000
  -0.250   0.1733   0.02174   0.01130  -0.0574   0.9120   1.0000
   0.000   0.2044   0.02202   0.01139  -0.0584   0.9040   1.0000
   0.250   0.2336   0.02231   0.01153  -0.0590   0.8956   1.0000
   0.500   0.2693   0.02257   0.01165  -0.0608   0.8885   1.0000
   0.750   0.2954   0.02286   0.01183  -0.0607   0.8788   1.0000
   1.000   0.3303   0.02310   0.01199  -0.0622   0.8712   1.0000
   1.250   0.3599   0.02335   0.01218  -0.0627   0.8616   1.0000
   1.500   0.3871   0.02360   0.01239  -0.0627   0.8513   1.0000
   1.750   0.4192   0.02378   0.01255  -0.0635   0.8422   1.0000
   2.000   0.4512   0.02392   0.01269  -0.0641   0.8325   1.0000
   2.500   0.5049   0.02426   0.01310  -0.0634   0.8089   1.0000
   2.750   0.5336   0.02434   0.01322  -0.0633   0.7969   1.0000
   3.000   0.5629   0.02436   0.01330  -0.0631   0.7847   1.0000
   3.250   0.5920   0.02433   0.01338  -0.0627   0.7718   1.0000
   3.500   0.6201   0.02427   0.01342  -0.0621   0.7579   1.0000
   3.750   0.6472   0.02419   0.01345  -0.0613   0.7429   1.0000
   4.000   0.6742   0.02408   0.01346  -0.0604   0.7271   1.0000
   4.250   0.7018   0.02391   0.01347  -0.0595   0.7107   1.0000
   4.500   0.7304   0.02367   0.01336  -0.0586   0.6937   1.0000
   4.750   0.7539   0.02362   0.01345  -0.0571   0.6732   1.0000
   5.000   0.7812   0.02340   0.01337  -0.0559   0.6523   1.0000
   5.250   0.8050   0.02333   0.01344  -0.0544   0.6274   1.0000
   5.500   0.8299   0.02323   0.01353  -0.0529   0.5996   1.0000
   5.750   0.8553   0.02314   0.01351  -0.0514   0.5682   1.0000
   6.000   0.8777   0.02327   0.01368  -0.0496   0.5312   1.0000
   6.250   0.8993   0.02351   0.01389  -0.0477   0.4909   1.0000
   6.500   0.9188   0.02397   0.01426  -0.0458   0.4490   1.0000
   6.750   0.9363   0.02464   0.01489  -0.0437   0.4072   1.0000
   7.000   0.9520   0.02549   0.01562  -0.0417   0.3675   1.0000
   7.250   0.9665   0.02646   0.01649  -0.0396   0.3309   1.0000
   7.500   0.9802   0.02752   0.01750  -0.0376   0.2958   1.0000
   7.750   0.9928   0.02868   0.01860  -0.0356   0.2635   1.0000
   8.000   1.0044   0.02992   0.01978  -0.0335   0.2333   1.0000
   8.250   1.0153   0.03124   0.02107  -0.0314   0.2041   1.0000
   8.500   1.0249   0.03266   0.02248  -0.0293   0.1761   1.0000
   8.750   1.0322   0.03420   0.02404  -0.0270   0.1510   1.0000
   9.000   1.0376   0.03590   0.02572  -0.0247   0.1255   1.0000
   9.250   1.0408   0.03780   0.02756  -0.0224   0.1007   1.0000
   9.500   1.0429   0.03989   0.02958  -0.0204   0.0780   1.0000
   9.750   1.0460   0.04215   0.03180  -0.0186   0.0630   1.0000
  10.000   1.0513   0.04464   0.03438  -0.0168   0.0528   1.0000
  10.250   1.0575   0.04719   0.03700  -0.0152   0.0472   1.0000
  10.500   1.0664   0.04964   0.03972  -0.0138   0.0422   1.0000
  10.750   1.0686   0.05221   0.04229  -0.0126   0.0387   1.0000
  11.000   1.0767   0.05510   0.04553  -0.0113   0.0357   1.0000
  11.250   1.0822   0.05825   0.04904  -0.0101   0.0337   1.0000
  11.500   1.0843   0.06166   0.05276  -0.0092   0.0327   1.0000
  11.750   1.0816   0.06546   0.05685  -0.0086   0.0317   1.0000
  12.000   1.0757   0.06954   0.06130  -0.0084   0.0313   1.0000
  12.250   1.0662   0.07406   0.06610  -0.0087   0.0310   1.0000
  12.500   1.0529   0.07922   0.07151  -0.0098   0.0307   1.0000
  12.750   1.0368   0.08508   0.07763  -0.0119   0.0308   1.0000
  13.000   1.0175   0.09192   0.08470  -0.0151   0.0310   1.0000
  13.250   0.9954   0.09998   0.09290  -0.0197   0.0314   1.0000
  13.500   0.9710   0.10962   0.10272  -0.0256   0.0320   1.0000
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