A study of the effect of surface defect caused by impact load from shock wave on wing design in transonic speeds using classical plate theory

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Dr. Fathi Al-Shamma
Dr. Fathi Al-Shamma
2
Dr.Fathi Alshamma
Dr.Fathi Alshamma
3
Assma Hassan
Assma Hassan
1 baghdad university Iraq

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In this research the aerodynamic load have been determined in critical transonic speeds taking into consideration the shock wave effect along X-29 aircraft wing , first by using computational fluid dynamics in fluent program, then taking these results as an applied loads in the classical plate theory (c.p.t) to estimate these stresses depending on time and speeds of impact load as a major parameter, and a numerical method using F.E.M (Ansys 10 ) for confirming the results that obtained from analytical solution. Results shows that the value of pressure coefficient along the wing using (c.p.t) is higher then the experimental one which is more save in design for transonic flow and its appeared that the position of maximum effect of shock wave on wing section depends on angle of attack , sweep angle and duration time of the shock wave load .

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No external funding was declared for this work.

Conflict of Interest

The authors declare no conflict of interest.

Ethical Approval

No ethics committee approval was required for this article type.

Data Availability

Not applicable for this article.

Dr. Fathi Al-Shamma. 2011. \u201cA study of the effect of surface defect caused by impact load from shock wave on wing design in transonic speeds using classical plate theory\u201d. Global Journal of Research in Engineering - A : Mechanical & Mechanics GJRE-A Volume 11 (GJRE Volume 11 Issue A7): .

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Crossref Journal DOI 10.17406/gjre

Print ISSN 0975-5861

e-ISSN 2249-4596

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v1.2

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December 23, 2011

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English

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In this research the aerodynamic load have been determined in critical transonic speeds taking into consideration the shock wave effect along X-29 aircraft wing , first by using computational fluid dynamics in fluent program, then taking these results as an applied loads in the classical plate theory (c.p.t) to estimate these stresses depending on time and speeds of impact load as a major parameter, and a numerical method using F.E.M (Ansys 10 ) for confirming the results that obtained from analytical solution. Results shows that the value of pressure coefficient along the wing using (c.p.t) is higher then the experimental one which is more save in design for transonic flow and its appeared that the position of maximum effect of shock wave on wing section depends on angle of attack , sweep angle and duration time of the shock wave load .

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A study of the effect of surface defect caused by impact load from shock wave on wing design in transonic speeds using classical plate theory

Dr.Fathi Alshamma
Dr.Fathi Alshamma
Assma Hassan
Assma Hassan

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