Aerodynamic calculation of the ultralight suborbital rocket K110 SU
Heading:
| 1Proroka, VA, 2Alekseyenko, SV 1Oles Honchar National University of Dnipro, Dnipro, Ukraine 2National Technical University “Dnipro Polytechnic”, Dnipro, Ukraine |
| Space Sci. & Technol. 2024, 30 ;(6):20-30 |
| https://doi.org/10.15407/knit2024.06.020 |
| Publication Language: English |
Abstract: Calculation of aerodynamic characteristics of aircraft is an important stage in solving the tasks of their design and refinement. Aerodynamic computations are required to determine the optimal aerodynamic shape, conduct ballistic computations, develop the control system, strength calculations, and solutions for other tasks arising in the design of aircraft. In this study, the aerodynamic characteristics of suborbital rocket K110 SU were analyzed using the method of three-dimensional Navier-Stokes equations averaged according to Reynolds. For closing up the system of equations, the SST k-ω model of turbulence was chosen. A numerical solution of the Navier-Stokes equation was obtained with the help of the control volume method. In calculations, the method of the 2nd order of approximation in spatial variables was used. Verification of this method was done by comparison of the obtained computational results with known experimental data. For the developed structural and compositional layout of the rocket, the dependence of the frontal drag on the Mach number and roughness of the surface was investigated. Peculiarities of the structure of the flow with consideration of the shape of the fairing and aerospike were determined, and their influence on the aerodynamics of the vehicle was analyzed. Dependences of aerodynamic properties on the velocity of flight at subsonic, transonic, and supersonic modes of the airflow were obtained.
Based on the obtained results, recommendations for the choice of geometric parameters of ultralight suborbital rockets were developed from the point of view of minimization of the head drag factor during the flight on a given trajectory within the determined range of Mach numbers. The obtained results can be used in designing new and improving existing samples of ultralight suborbital rockets.
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| Keywords: AERODYNAMIC COEFFICIENTS, aerodynamics, COMPUTATIONAL FLUID DYNAMICS, NUMERIC METHODS, SUBORBITAL ROCKET |
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