Parameterization and optimization design of a two-dimensional axisymmetric hypersonic inlet

Abstract

Optimization method, as a promising way to improve inlet aerodynamic performance, has received increasing attention. The present research is undertaken to design a two-dimensional axisymmetric hypersonic inlet using parametric optimization. The inlet configuration is parameterized and optimized in consideration of total pressure recovery and starting performance. A Pareto front is obtained by solving the multi-objective optimization problem. Then, the flow structures of the optimized inlets are analyzed and the starting performances are evaluated. Results show that the total pressure loss mainly occurs in the internal contraction section, especially near the inlet entrance, and therefore the total pressure recovery coefficient can be greatly improved by decreasing external compression. As a result, the guidance for designing high-performance inlets is concluded. Besides, it is found that as the internal contraction ratio increases, the inlet starting ability becomes worse, which attributes to the larger separation bubble at the inlet entrance. Finally, the total pressure recovery coefficient and the starting Mach number of the optimized inlets are obtained, which can be a reference for engineering design.

Aerodynamic optimization design of low reynolds number aerofoils based on induced laminar separation

“…Common aerofoil description methods include the Bezier curve, B-spline curve, Non-Uniform Rational B-spline (NURBS) surfaces, Hicks-Henne bump functions [10] , Trigonometric functions, Specific discipline functions, basis vectors, and FFD. Parametric description methods have undergone significant development, and optimizing low Reynolds numbers requires consideration of their specificity.…”

Effects of Cowl Lip Angle on Starting Performances for a Mixed-Compression Two-Dimensional Axisymmetric Hypersonic Inlet

“…In this section, the influences of cowl lip angle on starting performance are investigated for the inlets with ICR ranges from 1.8 to 2.2. Herein, the inlet ICR can be controlled by adjusting the external/internal compression walls, and the design method is described in detail in [7]. Figure 14 illustrates the effects of the cowl lip angle on starting performance of inlets with various ICRs.…”

“…As a key component, the inlet is used to capture and compress air, and then sent the airflow to the combustion chamber. A well-designed inlet is one that can capture adequate airflow with high total pressure recovery performance and low distortion [7,8]. However, when an unstart emerges, the inlet experiences rapid reductions in captured airflow and total pressure recovery performance, which further results in thrust decline or even engine flameout [9][10][11].…”