A5103035838- Fluid Dynamics and Turbulent Flows
- Computational Fluid Dynamics and Aerodynamics
- Aerodynamics and Acoustics in Jet Flows
- Particle Dynamics in Fluid Flows
- Plasma and Flow Control in Aerodynamics
- Advanced Vision and Imaging
- Higher Education and Teaching Methods
- Gas Dynamics and Kinetic Theory
- Inertial Sensor and Navigation
- Yersinia bacterium, plague, ectoparasites research
- GNSS positioning and interference
- Meteorological Phenomena and Simulations
- Advanced Computational Techniques and Applications
- Advanced Image Processing Techniques
- Genomics and Phylogenetic Studies
- Fluid Dynamics and Vibration Analysis
- RNA and protein synthesis mechanisms
- Image Enhancement Techniques
- Plant Water Relations and Carbon Dynamics
- Advanced Decision-Making Techniques
- Aerodynamics and Fluid Dynamics Research
- Education and Work Dynamics
- Ideological and Political Education
- Railway Systems and Energy Efficiency
- Transportation Systems and Logistics
China Aerodynamics Research and Development Center
2016-2022
National University of Defense Technology
2013-2015
CTI Engineering (Japan)
2014-2015
Gansu Provincial Maternal and Child Health Hospital
2015
Nanyang Normal University
2014
Yantai Nanshan University
2014
Northeast Agricultural University
2013
Central Compilation & Translation Bureau
2003
A wind tunnel experiment and large eddy simulation are carried out for the investigations of a Mach 5 boundary layer transition flow induced by distributed ramp shaped roughness elements. The is using nano-tracer planar laser scattering technique to capture coherent structures, whereas implicit in same conditions. Dominant unstable modes analyzed. Comparisons show that major frequencies obtained from computation generally agree with each other, although occurs much earlier tunnel. Coherent...
Experimental investigations of supersonic laminar/turbulent flow over a compression ramp are carried out in Mach 3.0 wind tunnel, the angles 25 degrees and 28 degrees. Fine structures holistic field local regions visualized via nanoparticle-tracer based planar laser scattering (NPLS) technique, some typical such as boundary layer, shear separation shock, recirculation zone reattachment shock visible clearly, wall pressure coefficient laminar is measured. The angle development layer after...
The effect of micro-ramp control on fully developed turbulent flow over a forward-facing step (FFS) is investigated in supersonic low-noise wind tunnel at Mach number 3 using nano-tracer planar laser scattering (NPLS) and particle image velocimetry (PIV) techniques. High spatiotemporal resolution images the average velocity profiles FFS with without micro-ramps are captured. fine structures both cases, including coherent boundary layer large-scale hairpin-like vortices originated from as...
The effects of the micro-ramps on supersonic turbulent flow over a forward-facing step (FFS) was experimentally investigated in low-noise wind tunnel at Mach number 3 using nano-tracer planar laser scattering (NPLS) and particle image velocimetry (PIV) techniques. High spatiotemporal resolution images velocity fields testing model were captured. fine structures their spatial evolutionary characteristics without with revealed compared. large-scale generated by can survive downstream FFS...
The coherent structures of flow over a double elliptic surface are experimentally investigated in supersonic low-noise wind tunnel at Mach number 3 using nano-tracer planar laser scattering (NPLS) and particle image velocimetry (PIV) techniques. High spatiotemporal resolution images velocity fields both laminar turbulent inflows the test model captured. Based on time-correlation images, spatial temporal evolutionary characteristics investigated. NPLS good agreement with fluctuation by PIV....
The classical problem of flat plate boundary layer which involves turbulence and transition is still hot, a mass work should be done to reach high accuracy measurement this flow, especially under the condition velocity. In present paper, application nano-based planar laser scattering (NPLS) method in hypersonic short-duration facility explored, then studied. Mach number main flow 7.3, total pressure 4.8 MPa, temperature 680 K. Through analysis tests, synchronization control NPLS system with...
Drag reduction technology plays a significant role in extending the flight range for high-speed vehicle. A wave drag strategy via heat addition to blunt body with spike was proposed and numerically validated. The is simulated continuous heating confined area upstream of body. effects on three flow conditions ( <a:math xmlns:a="http://www.w3.org/1998/Math/MathML" id="M1"> <a:mi>M</a:mi> <a:mo>=</a:mo> <a:mn>3.98</a:mn> <a:mo>,</a:mo> <a:mn>5</a:mn> <a:mn>6</a:mn> </a:math> ) were compared,...
Abstract An experimental investigation on the flow separation of a hypersonic laminar boundary layer over compression ramp with angles 32 deg, 36 and 40 deg is carried out in Mach 5 wind tunnel. The detailed structures are measured by particle image velocimetry (PIV), some typical structures, such as shear layer, shock, recirculation zone reattachment clearly captured. In flow, does not experience separation, always attaches to surface. When angle increases appears shock arise within field....