A5011943132- Computational Fluid Dynamics and Aerodynamics
- Fluid Dynamics and Turbulent Flows
- Rocket and propulsion systems research
- Combustion and flame dynamics
- Plasma and Flow Control in Aerodynamics
- Advanced Combustion Engine Technologies
- Aerodynamics and Acoustics in Jet Flows
- Gas Dynamics and Kinetic Theory
- Fluid Dynamics and Heat Transfer
- Heat transfer and supercritical fluids
- Combustion and Detonation Processes
- Electrohydrodynamics and Fluid Dynamics
- Advanced Sensor and Control Systems
- Energetic Materials and Combustion
- Hydraulic and Pneumatic Systems
- Industrial Technology and Control Systems
- Turbomachinery Performance and Optimization
- Plant Surface Properties and Treatments
- Advanced Sensor Technologies Research
- Real-time simulation and control systems
- Particle Dynamics in Fluid Flows
- Radiative Heat Transfer Studies
- Pesticide Residue Analysis and Safety
- Hydrology and Sediment Transport Processes
- Near-Field Optical Microscopy
National University of Defense Technology
2015-2024
National Engineering Research Center for Information Technology in Agriculture
2013
Center for Information Technology
2012
A liquid–liquid pintle injector element was used as the test object to analyze its spray characteristics from four aspects: morphology, dynamic characteristics, velocity distribution, and relation between cone angle momentum ratio. Experimental results indicated that range of area can be adjusted using total When ratio changes in scale 0.04–0.2, remains 45° 70°, where semi-open fan-shaped exhibits most significant uniform energy largest high-speed range, best atomization. The smaller block...
The separation induced by shock wave/boundary layer interactions (SWBLI) is detrimental to the performance of flow field, and thus, needs be reduced using passive or active approaches. In this study, authors numerically evaluate control steady pulsed micro-jets capture mechanism three-dimensional (3D) SWBLIs. volume zone accurately calculated assess effect. results predicted 3D Reynolds-averaged Navier–Stokes equations coupled with two-equation κ-ω turbulence model shear stress transport...
NanoAccepted Papers No AccessMolecular dynamics (ReaxFF MD) simulation of hydrogen effects on air heater combustionLiu Miaoe and Shen ChibingLiu Chibinghttps://orcid.org/0000-0003-2310-1720 Search for more papers by this author https://doi.org/10.1142/S1793292025500274Cited by:0 (Source: Crossref) PreviousNext AboutFiguresReferencesRelatedDetailsPDF/EPUB ToolsAdd to favoritesDownload CitationsTrack CitationsRecommend Library ShareShare onFacebookTwitterLinked InRedditEmail Cite Recommend We...
A supersonic mixing layer at a convective Mach number of 0.8 was investigated by large eddy simulation. Turbulent structures and statistics the interacting with an oblique shock different strengths in self-preserving stage were compared shock-free layer. An inflection point arises on velocity profiles region where incident wave impinges, addition to three points existing It is caused hairpin vortices induced through baroclinic mechanism interaction wave. However, disappear quickly within...
Schlieren and shadowgraph visualizations of flowfields in a typical configuration supersonic film cooling backward-facing slot were conducted Mach 2.95 continuous-suction wind tunnel, with the gas tangentially ejected through half-Laval nozzle 1.5. The after step without injection coolant measured paper, including delivery pressures matched unmatched conditions mainstream, respectively. effects different injecting on these also analyzed. A clear visual image was obtained, characteristics...
This study conducts a comparison between novel waverider generated from axisymmetric supersonic flow past pointed von Karman ogive and conventional cone-derived the cone. First, is obtained by sharpening blunt nose of original to point. Then, cone with same shock wave radius at base plane as that when it travels designated speed designed. Both flows are calculated using method characteristics, two fields employed new basic waveriders, respectively. Second, field ogive, streamline tracing...
Large-scale vortices downstream of a lobed mixer are investigated experimentally using nanoparticle-based planar laser scattering experimental system. The results contrasted with additional measurements flat plate and convoluted plate. Three streamwise form the due to pressure difference between peak trough regions trailing edge. This is not case for plate, where structures suppressed do appear downstream. Comparison vortex sizes indicates that contribute almost 80% mixing enhancement, which...
Experiments are conducted on a supersonic mixing layer with two lobed mixers, which designed following the concept of shock-eliminating combustor. Instantaneous images were obtained to examine evolution process large-scale vortices downstream mixers. The results show that no streamwise appeared mixer penetration angle approximately 6.7° owing smaller pressure difference between peak and trough regions compared rectangular (RLM). However, it provides similar enhancement as an RLM. Streamwise...