Singh, Manish K and Ramesh, V and Balakrishnan, N (2015) Implicit scheme for meshless compressible Euler solver. In: ENGINEERING APPLICATIONS OF COMPUTATIONAL FLUID MECHANICS, 9 (1). pp. 382-398.
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In this paper, an implicit scheme is presented for a meshless compressible Euler solver based on the Least Square Kinetic Upwind Method (LSKUM). The Jameson and Yoon's split flux Jacobians formulation is very popular in finite volume methodology, which leads to a scalar diagonal dominant matrix for an efficient implicit procedure (Jameson & Yoon, 1987). However, this approach leads to a block diagonal matrix when applied to the LSKUM meshless method. The above split flux Jacobian formulation, along with a matrix-free approach, has been adopted to obtain a diagonally dominant, robust and cheap implicit time integration scheme. The efficacy of the scheme is demonstrated by computing 2D flow past a NACA 0012 airfoil under subsonic, transonic and supersonic flow conditions. The results obtained are compared with available experiments and other reliable computational fluid dynamics (CFD) results. The present implicit formulation shows good convergence acceleration over the RK4 explicit procedure. Further, the accuracy and robustness of the scheme in 3D is demonstrated by computing the flow past an ONERA M6 wing and a clipped delta wing with aileron deflection. The computed results show good agreement with wind tunnel experiments and other CFD computations.
|Item Type:||Journal Article|
|Additional Information:||Copy right for this article belongs to the HONG KONG POLYTECHNIC UNIV, DEPT CIVIL & STRUCTURAL ENG, HUNG HOM, KOWLOON, HONG KONG, 00000, PEOPLES R CHINA|
|Keywords:||implicit scheme; meshless Euler solver; LSKUM; matrix-free formulation; NACA 0012 airfoil; ONERA M6 wing; clipped delta wind; aileron deflection|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||31 Oct 2015 05:15|
|Last Modified:||31 Oct 2015 05:15|
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