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SD7084 (9.6%) (sd7084-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SD7084 (9.6%) (sd7084-il)
Reynolds number: 50,000
Max Cl/Cd: 35.55 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd7084-il-50000-n5.txt
Download as CSV file: xf-sd7084-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7084 (9.6%)                                   
  
 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  -0.4512   0.08876   0.08199  -0.0377   1.0000   0.0553
  -8.500  -0.4493   0.08523   0.07847  -0.0377   1.0000   0.0545
  -8.250  -0.4534   0.08138   0.07470  -0.0389   1.0000   0.0538
  -8.000  -0.4587   0.07745   0.07083  -0.0401   1.0000   0.0530
  -7.750  -0.4647   0.07333   0.06675  -0.0412   1.0000   0.0523
  -7.500  -0.4710   0.06935   0.06277  -0.0418   1.0000   0.0516
  -7.250  -0.4773   0.06534   0.05871  -0.0419   1.0000   0.0509
  -7.000  -0.4820   0.06140   0.05468  -0.0416   1.0000   0.0504
  -6.750  -0.4848   0.05747   0.05058  -0.0410   1.0000   0.0499
  -6.500  -0.4849   0.05360   0.04646  -0.0400   1.0000   0.0495
  -6.250  -0.4818   0.04990   0.04246  -0.0389   1.0000   0.0492
  -6.000  -0.4754   0.04639   0.03861  -0.0376   1.0000   0.0492
  -5.750  -0.4660   0.04321   0.03503  -0.0363   1.0000   0.0499
  -5.500  -0.4540   0.04039   0.03176  -0.0349   1.0000   0.0517
  -5.250  -0.4396   0.03770   0.02852  -0.0335   1.0000   0.0540
  -5.000  -0.4228   0.03529   0.02554  -0.0320   1.0000   0.0552
  -4.750  -0.4043   0.03298   0.02286  -0.0307   1.0000   0.0560
  -4.500  -0.3852   0.03098   0.02065  -0.0295   1.0000   0.0574
  -4.250  -0.3650   0.02935   0.01881  -0.0283   1.0000   0.0593
  -4.000  -0.3441   0.02793   0.01714  -0.0270   1.0000   0.0616
  -3.750  -0.3228   0.02669   0.01566  -0.0257   1.0000   0.0653
  -3.500  -0.3020   0.02563   0.01449  -0.0245   1.0000   0.0716
  -3.250  -0.2811   0.02477   0.01351  -0.0233   1.0000   0.0795
  -3.000  -0.2590   0.02382   0.01250  -0.0224   1.0000   0.0881
  -2.750  -0.2375   0.02301   0.01164  -0.0215   1.0000   0.1057
  -2.500  -0.2162   0.02209   0.01088  -0.0208   1.0000   0.1441
  -2.250  -0.1892   0.02050   0.01031  -0.0218   0.9969   0.3052
  -2.000  -0.1630   0.01914   0.01041  -0.0212   0.9891   0.6149
  -1.750  -0.0893   0.01857   0.01033  -0.0276   0.9878   1.0000
  -1.500  -0.0479   0.01884   0.01011  -0.0310   0.9772   1.0000
  -1.250  -0.0065   0.01910   0.00999  -0.0343   0.9666   1.0000
  -1.000   0.0360   0.01936   0.00992  -0.0377   0.9560   1.0000
  -0.750   0.0752   0.01956   0.00984  -0.0403   0.9440   1.0000
  -0.500   0.1133   0.01973   0.00980  -0.0427   0.9314   1.0000
  -0.250   0.1513   0.01988   0.00976  -0.0449   0.9185   1.0000
   0.000   0.1894   0.01999   0.00970  -0.0470   0.9053   1.0000
   0.250   0.2274   0.02006   0.00966  -0.0490   0.8917   1.0000
   0.500   0.2633   0.02011   0.00959  -0.0504   0.8775   1.0000
   0.750   0.2976   0.02011   0.00951  -0.0514   0.8626   1.0000
   1.000   0.3309   0.02008   0.00942  -0.0521   0.8472   1.0000
   1.250   0.3636   0.02001   0.00931  -0.0526   0.8314   1.0000
   1.500   0.3934   0.01994   0.00920  -0.0524   0.8141   1.0000
   1.750   0.4210   0.01990   0.00913  -0.0519   0.7951   1.0000
   2.000   0.4508   0.01981   0.00902  -0.0516   0.7770   1.0000
   2.250   0.4802   0.01972   0.00892  -0.0512   0.7581   1.0000
   2.500   0.5072   0.01970   0.00888  -0.0504   0.7369   1.0000
   2.750   0.5364   0.01964   0.00878  -0.0498   0.7165   1.0000
   3.000   0.5625   0.01969   0.00884  -0.0489   0.6935   1.0000
   3.250   0.5892   0.01976   0.00888  -0.0480   0.6704   1.0000
   3.500   0.6159   0.01986   0.00892  -0.0471   0.6471   1.0000
   3.750   0.6404   0.02007   0.00910  -0.0460   0.6220   1.0000
   4.000   0.6649   0.02032   0.00935  -0.0449   0.5971   1.0000
   4.250   0.6894   0.02061   0.00958  -0.0439   0.5728   1.0000
   4.500   0.7133   0.02095   0.00988  -0.0428   0.5485   1.0000
   4.750   0.7364   0.02136   0.01028  -0.0417   0.5241   1.0000
   5.000   0.7596   0.02179   0.01073  -0.0407   0.5008   1.0000
   5.250   0.7827   0.02227   0.01119  -0.0396   0.4783   1.0000
   5.500   0.8052   0.02279   0.01174  -0.0386   0.4562   1.0000
   5.750   0.8281   0.02334   0.01228  -0.0376   0.4355   1.0000
   6.000   0.8505   0.02393   0.01292  -0.0366   0.4151   1.0000
   6.250   0.8727   0.02455   0.01365  -0.0357   0.3957   1.0000
   6.500   0.8952   0.02519   0.01432  -0.0347   0.3776   1.0000
   6.750   0.9167   0.02590   0.01513  -0.0337   0.3594   1.0000
   7.000   0.9380   0.02663   0.01596  -0.0327   0.3418   1.0000
   7.250   0.9591   0.02739   0.01682  -0.0316   0.3250   1.0000
   7.500   0.9797   0.02816   0.01769  -0.0305   0.3086   1.0000
   7.750   1.0000   0.02897   0.01865  -0.0294   0.2926   1.0000
   8.000   1.0187   0.02986   0.01970  -0.0281   0.2759   1.0000
   8.250   1.0362   0.03077   0.02078  -0.0267   0.2589   1.0000
   8.500   1.0527   0.03169   0.02187  -0.0251   0.2419   1.0000
   8.750   1.0675   0.03260   0.02289  -0.0235   0.2247   1.0000
   9.000   1.0800   0.03358   0.02399  -0.0215   0.2068   1.0000
   9.250   1.0894   0.03465   0.02526  -0.0194   0.1874   1.0000
   9.500   1.0958   0.03574   0.02646  -0.0170   0.1683   1.0000
   9.750   1.0992   0.03709   0.02794  -0.0144   0.1477   1.0000
  10.000   1.0984   0.03859   0.02944  -0.0116   0.1290   1.0000
  10.250   1.0952   0.04045   0.03131  -0.0089   0.1113   1.0000
  10.500   1.0910   0.04270   0.03358  -0.0066   0.0952   1.0000
  10.750   1.0854   0.04534   0.03622  -0.0047   0.0823   1.0000
  11.000   1.0793   0.04823   0.03911  -0.0034   0.0726   1.0000
  11.250   1.0724   0.05139   0.04228  -0.0026   0.0651   1.0000
  11.500   1.0673   0.05483   0.04589  -0.0021   0.0585   1.0000
  11.750   1.0609   0.05839   0.04948  -0.0022   0.0541   1.0000
  12.000   1.0548   0.06230   0.05353  -0.0025   0.0503   1.0000
  12.250   1.0498   0.06635   0.05781  -0.0030   0.0470   1.0000
  12.500   1.0446   0.07051   0.06211  -0.0038   0.0447   1.0000
  12.750   1.0386   0.07478   0.06642  -0.0049   0.0426   1.0000
  13.000   1.0329   0.07935   0.07111  -0.0061   0.0411   1.0000
  13.250   1.0232   0.08500   0.07707  -0.0083   0.0398   1.0000
  13.500   1.0123   0.09101   0.08334  -0.0110   0.0389   1.0000
  13.750   1.0000   0.09758   0.09014  -0.0141   0.0386   1.0000
  14.000   0.9855   0.10495   0.09772  -0.0180   0.0385   1.0000
  14.250   0.9681   0.11340   0.10636  -0.0226   0.0387   1.0000
  14.500   0.9491   0.12281   0.11593  -0.0278   0.0394   1.0000
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