SINGLE-LAYER MARCHING ALGORITHM TO CALCULATE SUPERSONIC FLOW ABOUT ROCKETS WITH THE COMPUTATIONAL REGION DIVIDED INTO SEVERAL SUBREGIONS
Keywords:
algorithm, marching method, rocket, structure, wing, rudder, stabilizer, superstructure, computational region, computational subregion, supersonic flow, numerical calculation, flow field.Abstract
This paper presents a single-layer marching algorithm to calculate supersonic flow about rockets that may be equipped with wings, stabilizers, rudders, and superstructures. In this algorithm, the rocket along its axis is divided into sections of two types: sections along the rocket structure without additional elements (type 1 sections), which are calculated using a standard one-zone algorithm, and sections along the rocket structure with additional elements, which are calculated using a multizone algorithm. To calculate supersonic flow about additional elements of arbitrary shape (wings, stabilizers, rudders, and superstructures) installed on the rocket body, use is made of a Cartesian system of coordinates with the computational region divided into several computational subregions (CSRs), whose outer boundaries are the rocket structure surface, the surfaces of the additional elements, and the bow shock front. In each specific case, the method of division of the computational region into several CSRs is determined by the shape of the additional elements installed on the rocket structure along the type 2 section under consideration. Five methods are proposed to divide the computational region into CSRs using Cartesian, cylindrical, or polar coordinates for constructing computational meshes in different CSRs, which is a reasonably universal approach to calculating supersonic flow about rockets with variously shaped additional elements. Based on the above algorithm, the development of software is underway, whose use will greatly reduce the time taken for numerical calculations of supersonic flow about rockets with variously shaped wings, stabilizers, rudders, and superstructures to a design accuracy. The advantage of the software under development is the promptness of parametric calculations, which allows one to greatly reduce the time taken for rocket pre-characterization at the tryout stage of the design parameters of rocket components.
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