Authors
Abstract
In this study, a theoretical analysis was used to investigate the wing aerodynamic analysis and the best structural configuration of a delta wing with a satisfaction for the design requirements.
The analysis was related with both the aerodynamic and structural design considerations such that, in the aerodynamic approach, an estimation of the pressure distribution and aerodynamic design characteristics of the wing in the supersonic potential flow was done by using low order panel method for different angles of attack. In the structural part, five geometric models of wing were tested for three types of aerodynamic loading by changing the angle of attack from (10-14)" by using the finite element teclinique to find stresses and deformations.
The results showed that a clear pattern of increasing peak pressure with angle of attack in agreement with increasing strength of the leading edge vortex. Also, the results showed that, the stresses generally decrease with increasing each of the thickness of wing shell, and number of spars and ribs chordwisely and spanwisely respectively. These results were compared with those of published data and it was found that they are accurate and reliable.
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