Neural Networks and Rules-based Systems used to Find Rational and Scientific Correlations between being Here and Now with Afterlife Conditions
Neural Networks and Rules-based Systems used to Find Rational and
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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 .
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): .
Crossref Journal DOI 10.17406/gjre
Print ISSN 0975-5861
e-ISSN 2249-4596
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Total Score: 107
Country: Nigeria
Subject: Global Journal of Research in Engineering - A : Mechanical & Mechanics
Authors: Dr.Fathi Alshamma, Assma Hassan (PhD/Dr. count: 1)
View Count (all-time): 192
Total Views (Real + Logic): 5464
Total Downloads (simulated): 2756
Publish Date: 2011 12, Fri
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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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