Analysis of Aerodynamic Characteristics of the Rocket-Target for the „Stinger” System

A CFD Study of the Aerodynamic Characteristics of Twardowsky and FOK Rockets

“…the distance from the base of the cylinder to the center of the semi-sphere was equal to 4 times the rockets' length. some studies in the literature have been successful with domains of similar sizes [1,6,12,14,17,19,21], even with comparable and AoA regimes [7], while others used larger control volumes even for lesser AoA ranges [3,4,10,13,15,16,18,20].…”

“…For the purpose of this campaign, a density-based solver was used for all cases due to the compressibility effects taking place at M > 0.3. the sst k -ω turbulent model was chosen for the simulations because it is a common choice in the literature regarding rocket aerodynamics [5,7,8,12,[15][16][17][18][19][20][21][22]. other turbulence models, such as the k -ω [4,14,15,20], spalart-Allmaras [1,4,8,22] and k -ϵ models [2-4, 6, 8, 10, 11, 13, 20], have also found use and been directly compared to each other [4,8,20,22], with k -ω often being deemed preferable [8,20].…”

“…CFD has been used to approach many problems related to the aerodynamics of rockets. research topics have included estimating aerodynamic loads related to performance [1,4,5,7,10,12,[15][16][17][18][19][20][21], longitudinal stability [1,5,10,12,13,15,17,19,27] and roll control [3,6,11,14,15], but also more general themes like aeroelasticity [5,18,20] and the influence of various design elements, including nose cone geometries [16], grid fins [2], curved fins [7], spinning tail configurations [3,14] and canards [1,3,5,10,11,13,15,18,21]. some studies have explored the appropriateness of various CFD methods with regard to rocket aerodynamics [4,8,20,…”

Utilization of CFD for the Aerodynamic Analysis of a Subsonic Rocket

“…The first layer thickness of the inflation layer is 0.0018 mm. This parameter is kept as small as possible so that the first layer is located close to the rocket body [8]. It is mentioned above that this structure is necessary in order to successfully resolving the boundary layer.…”

“…The airflow characteristics such as airflow velocity, flow rate, pressure, drag force, etc. affect substantially the exterior ballistics of the rocket [8]. The aerodynamic coefficients, which are drag and lift coefficients, are dimensionless quantities which are used to determine the aerodynamic characteristics of a structure.…”