Influence of Sweep Angle on the Surface Pressure of Delta Wing Along Pivot Positions at Hypersonic Mach Numbers

Abstract

This study focuses on analyzing pressure distribution across the wing surface under different flight conditions. The distribution of surface pressure plays a crucial role in determining the performance of a delta wing. The outcomes of this research will be beneficial for stability assessment and enhancing performance during the aircraft design phase. The paper illustrates the impact of high supersonic Mach numbers, angles of incidence, and specific locations along the three-dimensional delta wing. Strips located at various span-wise positions are treated independently based on a strip theory, which when combined with hypersonic similitude, results in a piston theory. It is important to note that the current theory is only valid when the shock wave remains attached. Viscosity and wave reflection effects have not been taken into account in this particular study. The parameters considered in the study are the Mach numbers (M) in the range 4 to 7. Furthermore, consideration is given to the Angle of Incidence (θ), which varies between 5° to 25°. Along the Wings chord from 0.2 to 1, different points (h) record the pressure results (P2/P1). For numerical simulations, CFD was used, and simulated results at hypersonic Mach numbers matched well with analytical results.