Aerodynamics of porous airfoils and wings
This paper presents novel wind tunnel test results on the aerodynamics of a symmetric thin porous airfoil and a porous rectangular half wing using a symmetric thin airfoil as its cross section, obtained by a six-component force balance. The variation of lift coefficient, drag coefficient, pitching...
| Main Authors: | , , , |
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| Format: | Article |
| Language: | English English English |
| Published: |
SpringerLink
2018
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| Subjects: | |
| Online Access: | http://irep.iium.edu.my/64676/ http://irep.iium.edu.my/64676/ http://irep.iium.edu.my/64676/ http://irep.iium.edu.my/64676/1/Aerodynamics%20of%20permeable%20airfoils%20and%20wings-published.pdf http://irep.iium.edu.my/64676/7/64676_Aerodynamics%20of%20porous%20airfoils%20and%20wings_SCOPUS.pdf http://irep.iium.edu.my/64676/13/64676_Aerodynamics%20of%20porous%20airfoils%20and%20wings_WOS.pdf |
| Summary: | This paper presents novel wind tunnel test results on the aerodynamics of a symmetric thin porous
airfoil and a porous rectangular half wing using a symmetric thin airfoil as its cross section, obtained by a
six-component force balance. The variation of lift coefficient, drag coefficient, pitching moment, lift versus
drag, the gradient of lift, and location of the aerodynamic center with respect to the angle of attack are presented
as a function of the porosity. The data, where possible, are compared with the analytical results. The trend of
the experimental results behaves in the same manner as the analytical solution. The measured drag coefficients
of the airfoil and wing are also presented. The applicability of the standard equation relating the lift coefficient of a non-porous wing with that of a non-porous airfoil to the case of porous wings is verified by applying
the equation to porous wings and validating the results using experimental data. Lift slope decreases as the
porosity increases. The drag decreases at a low value of porosity and then increases as porosity increases. The
standard equation for obtaining the lift coefficient of a wing from the lift coefficient of an airfoil is applicable
and valid for porous wings and airfoils. |
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