A modi ed indicial functions approximation for nonlinear aeroelastic analysis

Q: How can I download an article?

To download an article from SID, first log in to the site, search for the article title, and click on the 'Download Article' option.

Q: How can I download an ISI article?

To download an ISI article on SID, enter the keyword or article title in the search bar, view the relevant results, click on the desired article, and select the 'Download Article' option.

Q: How can I access the SID database?

To access the SID database, visit SID.ir, create an account, and log in to access scientific resources.

Q: Is downloading articles from SID free?

Some articles on SID are available for free, while others require payment. Details are specified on the article's page.

NEJATI M.; SHOKROLLAHI S.; SHAMS SH.; SHAMS SH.; Torkaman r.

مرکز اطلاعات علمی Scientific Information Database (SID) - Trusted Source for Research and Academic Resources

Journal Paper

Paper Information

Journal: Scientia Iranica Year:2020 | Volume:27 | Issue:3 (Transactions B: Mechanical Engineering) Page(s): 1230-1254

Download Full-Text

View:

Download:

Cites:

Information Journal Paper

Title

A modi ed indicial functions approximation for nonlinear aeroelastic analysis

Author(s)

Keywords

Indicial aerodynamics

Subsonic ow

Limit cycle oscillation

Nonlinear aeroelastic

High aspect ratio

Abstract

The nonlinear dynamic response, Limit cycle oscillations (LCOs), of High-Aspect-Ratio (HAR) wings using novel Indicial aerodynamics in Subsonic ow was investigated. Using the nonlinear beam theory, the structural model was derived with in-plane and out-of-plane bending and torsional motions, all nonlinearities up to cubic order arising from large deformation, mass distribution, and cross-sectional mass imbalance. Based on new approximations of the indicial functions, a comprehensive unsteady aerodynamic model was used. Coupling such Indicial aerodynamics to nonlinear structural equations can result in a uni ed Nonlinear aeroelastic formulation in both incompressible and subsonic compressible ows. The e ects of ight conditions, wing tip initial disturbances, Sti ness Ratio (SR) between bending modes, and nonlinearity due to inertia and cross-sectional mass imbalance on the characteristics of LCO are discussed. The results showed that compressibility could a ect the LCO boundary up to 12 percent, which implied that appropriate Mach-dependent aerodynamics was required to achieve a more reasonable and realistic description of dynamic behavior of the system. It was observed that the presence of LCO before the linear utter speed depended on the initial disturbances as well as wing characteristics.

Multimedia

No record.

Cites

No record.

References

No record.

Cite

APA: Copy

NEJATI, M., SHOKROLLAHI, S., SHAMS, SH., SHAMS, SH., & Torkaman, r.. (2020). A modi ed indicial functions approximation for nonlinear aeroelastic analysis. SCIENTIA IRANICA, 27(3 (Transactions B: Mechanical Engineering)), 1230-1254. SID. https://sid.ir/paper/982769/en

Vancouver: Copy

NEJATI M., SHOKROLLAHI S., SHAMS SH., SHAMS SH., Torkaman r.. A modi ed indicial functions approximation for nonlinear aeroelastic analysis. SCIENTIA IRANICA[Internet]. 2020;27(3 (Transactions B: Mechanical Engineering)):1230-1254. Available from: https://sid.ir/paper/982769/en

IEEE: Copy

M. NEJATI, S. SHOKROLLAHI, SH. SHAMS, SH. SHAMS, and r. Torkaman, “A modi ed indicial functions approximation for nonlinear aeroelastic analysis,” SCIENTIA IRANICA, vol. 27, no. 3 (Transactions B: Mechanical Engineering), pp. 1230–1254, 2020, [Online]. Available: https://sid.ir/paper/982769/en

Related Journal Papers

No record.

Related Seminar Papers

No record.

Related Plans

No record.

Recommended Workshops