The Effect of Through-Hole Perforation of the Control Surfaces on the Aerodynamic Characteristics of a Supersonic Vehicle
Published: 01.07.2026
Authors: Kalugina M.D., Lutsenko A.Yu., Popov I.O.
Published in issue: #7(175)/2026
Category: Aviation and Rocket-Space Engineering | Chapter: Aerodynamics and Heat Transfer Processes in Aircrafts
Nowadays aerodynamic shield surfaces are becoming widely used for supersonic vehicle control and braking. A complicated flow structure appears near the shields. Particularly, there is a vortex separation from the shield surfaces which can lead to vehicle vibrations and damage. One way to reduce vortex formation is to perforate controls. The paper presents the numerical simulation results of the flow past cylinder-conic body with afterbody shield controls. Three models considered have different degrees of shields through-hole perforation. The simulation was performed using the SolidWorks Flow Simulation package. The body aerodynamic coefficients and flow structures were obtained at a freestream Mach number of 2,06 in the attack angle range from 0 to 12 degrees. It was found that the shields through-hole perforation leads to the decrease of flow separation zone ahead of the shields, the pressure redistribution over their surfaces, the bottom vortex structure displacement and its drift downstream. Longitudinal force coefficient decreases, while the normal force coefficient increases compared to the solid shields case.
EDN IKKJKE
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