Abstract
In this paper, a numerical simulation of a finned store separating from a wing-pylon configuration has been studied and validated. A dynamic unstructured tetrahedral mesh approach is accomplished by using three grid sizes to numerically solving the discretized three dimensional, inviscid and compressible Euler equations. The method used for computations of separation of an external store assuming quasi-steady flow condition. Computations of quasi-steady flow have been directly coupled to a six degree-of-freedom (6DOF) rigid-body motion code to generate store trajectories. The pressure coefficients at four different angular cuts and time histories of various trajectory parameters and wing pressure distribution during the store separation are compared for every grid size with published experimental data.
Highlights
Safe separation of a store from an aircraft is one of the major aerodynamic problems in the design and integration of a new store to an aircraft
The predicted computed trajectories are compared with a 1/20 scale wind-tunnel experimental data conducted at the Arnold Engineering Development Center (AEDC) [1] under transonic conditions (Mach number 95) at an altitude of 11,600 m and 0° angle of attack for a particular weapon configuration with appropriate ejection forces
The computations are started from t=0s for obtaining the aerodynamic forces and moments the solver is coupled with a 6-DOF code for the complete store trajectory prediction using quasi-steady approach
Summary
Safe separation of a store from an aircraft is one of the major aerodynamic problems in the design and integration of a new store to an aircraft. Many techniques for handling the computational domain with moving boundaries have been devised and are currently being used such as Cartesian approach [4,5,6,7], overset grids [8,9,10,11,12,13,14,15,16] and dynamic meshes [17,18,19,20,21,22,23,24,25,26,27]. The Cartesian approach implies the use of non-body-fitted volume meshes This method has one major drawback when conventional finite volume procedures are used, accuracy is compromised in the cut cells on the boundaries where any error in these regions leads to inaccurate prediction of performance [28]. The predicted computed trajectories are compared with a 1/20 scale wind-tunnel experimental data conducted at the Arnold Engineering Development Center (AEDC) [1] under transonic conditions (Mach number 95) at an altitude of 11,600 m and 0° angle of attack for a particular weapon configuration with appropriate ejection forces
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