Boundary Layer Stability Regime at DACCIWA Site Using Gradient Richardson Number

Artículos similares

Conceptual Design of Layered Distributed Propulsion System to Improve Power-Saving Benefit of Boundary-Layer Ingestion

Acceso

Zhiping Li, Yujiang Lu and Tianyu Pan

DPS (distributed propulsion system) utilizing BLI (boundary-layer ingestion) has shown great potential for reducing the power consumption of sustainable AAM (advanced air mobility), such as BWB (blended-wing body) aircraft. However, the ingesting boundar... ver más

Revista: Aerospace

Measurement of the Convection Velocities in a Hypersonic Turbulent Boundary Layer Using Two-Point Cylindrical-Focused Laser Differential Interferometer

Acceso

Ranran Huang, Tao Xue and Jie Wu

A two-point cylindrical-focused laser differential interferometer (2P-CFLDI) system and a conventional Z-type Schlieren were used to measure the hypersonic turbulent boundary layer on a flat plate at Mach number Ma = 6 and Reynolds number Re = 1.08 × 106... ver más

Revista: Aerospace

Aerodynamic Instabilities in High-Speed Air Intakes and Their Role in Propulsion System Integration

Acceso

Aristia L. Philippou, Pavlos K. Zachos and David G. MacManus

High-speed air intakes often exhibit intricate flow patterns, with a specific type of flow instability known as ?buzz?, characterized by unsteady shock oscillations at the inlet. This paper presents a comprehensive review of prior research, focused on un... ver más

Revista: Aerospace

Real Gas Effects on Receptivity to Roughness in Hypersonic Swept Blunt Flat-Plate Boundary Layers

Acceso

Yanxin Yin, Ruiyang Lu, Jianxin Liu and Zhangfeng Huang

Temperatures within the boundary layers of high-enthalpy hypersonic flows can soar to thousands or even tens of thousands of degrees, leading to significant real gas phenomena. Although there has been significant research on real gas effects on hypersoni... ver más

Revista: Aerospace

Numerical Study on the Corner Separation Control for a Compressor Cascade via Bionic Herringbone Riblets

Acceso

Peng Zhang, Rixin Cheng and Yonghong Li

Bionic herringbone riblets are applied to relieve the flow near the blade endwall in a linear compressor cascade under the incidence angle of -4° to 6° at a Reynolds number of 382,000. The herringbone riblets are placed at the endwall upstream of the bla... ver más

Revista: Aerospace

Artículos similares

Revistas destacadas