A5014181892- Computational Fluid Dynamics and Aerodynamics
- Fluid Dynamics and Turbulent Flows
- Wind and Air Flow Studies
- Turbomachinery Performance and Optimization
- Aerodynamics and Fluid Dynamics Research
- Rocket and propulsion systems research
- Fluid Dynamics and Vibration Analysis
- Wind Energy Research and Development
- Plasma and Flow Control in Aerodynamics
- Advanced Numerical Methods in Computational Mathematics
- Combustion and flame dynamics
- Real-time simulation and control systems
- Microwave Engineering and Waveguides
- Antenna Design and Analysis
- Gas Dynamics and Kinetic Theory
- Oil and Gas Production Techniques
- Aerospace Engineering and Control Systems
- Aeroelasticity and Vibration Control
- Vibration and Dynamic Analysis
- Fluid Dynamics Simulations and Interactions
- Superconducting and THz Device Technology
- Cyclone Separators and Fluid Dynamics
- Advanced Aircraft Design and Technologies
- Meteorological Phenomena and Simulations
- Lightning and Electromagnetic Phenomena
University of Toledo
2016-2025
Universitatea Națională de Știință și Tehnologie Politehnica București
2020
American Society For Engineering Education
2020
Hohai University
2012
Mississippi State University
2007-2010
The conventional helicopter rotor S-76 hover performance is numerically investigated using an unstructured grid Navier–Stokes computational fluid dynamics solver. Three tip configurations, including rectangular straight tip, swept tapered and with anhedral are investigated, the results validated experimental data. figure of merit predicted over a range blade collective angles from 4 through 10 deg mesh deformation method. A local correlation-based transition model stall delay both...
Aerodynamic interactions of the model NREL 5 MW offshore horizontal axis wind turbines (HAWT) are investigated using a high-fidelity computational fluid dynamics (CFD) analysis. Four turbine configurations considered; three-bladed upwind and downwind two-bladed configurations, which operate at two different rotor speeds 12.1 16 RPM. In present study, both steady unsteady aerodynamic loads, such as torque, blade hub bending moment, base tower moment tower, evaluated in detail to provide...
Aerodynamic performance of a fan-in-wing configuration in hover is numerically investigated using high-fidelity three-dimensional unsteady Reynolds-averaged Navier–Stokes flow solver based on unstructured grid technology. Fan-in-wing or ducted fan configurations offer the advantage capability with enhanced thrust comparing to open fans, but they suffer from reduced efficiency and levels at offdesign conditions. In this study, aerodynamic flowfield are over range blade pitch angles two...
Aerodynamic performance and flow physics of a Hover Validation Acoustic Baseline (HVAB) rotor is further investigated using hybrid RANS/LES simulation methods. A wall-adaptive local eddy-viscosity model (WALE) coupled with two Reynolds averaged Navier-Stokes models: the Spalart-Allmaras one-equation turbulence (SA) Menter Shear Stress Transport two-equation (SST). Computational results are validated experimental data compared RANS solutions in prediction HVAB hover.
An unstructured hybrid approach is developed aimed at computing viscous flows around helicopter rotors in hover and forward flight. A single rotor blade resolved through the Navier-Stokes solution with consideration of vortex interaction for faster economical computations. The near wake captured by analysis. influence other blades trailing vorticity far field accounted modeling them as a collection piece-wise linear bound elements. use such Navier-Stokes/vortex method allows an accurate...
A high-order improvement to an unstructured viscous CFD solver is evaluated and applied the computation of helicopter rotors in hover forward flight. The achieved by reconstructing flow variables at interface each control volume through polynomial approximations. reconstructed are used as basis values evaluate fluxes on sub-faces using a radial function interpolation. scheme for inviscid unsteady vortex travelling with free stream observed order accuracy. method also compute realistic rotor...
CFD/CSD coupled simulations are presented for a Bell M427 main rotor in both forward and maneuvering flight. The unstructured CFD code UNCLE is with the CSD DYMORE2.0 to perform aeroelastic analysis. Two coupling strategies evaluated demonstrated: loose rotors steady level flight tight undergoing maneuver. A Fluid-Structure Interface (FSI) handles information exchange directs operation of codes required results assessed test data, method verified by comparing obtained where fixed control...
Covers advancements in spacecraft and tactical strategic missile systems, including subsystem design application, mission analysis, materials structures, developments space sciences, processing manufacturing, operations, applications of technologies to other fields.
The full-scale XV-15 proprotor hover performance and flow transition phenomena are numerically investigated using an unsteady Reynolds-averaged Navier–Stokes solver. rotor figure of merit is predicted over a range blade collective angles, computed skin frictions on the surface compared with wind-tunnel experimental data. A grid resolution study performed to investigate impact mesh predictions baseline refined mesh. Langtry–Menter local correlation-based model used predict friction onset...
An effort to improve the numerical accuracy of high-order unstructured grid schemes is presented in present study. The basic concept construct a polynomial approximation using both solution variables and their gradients calculate Riemann fluxes on discontinuous interface. are then integrated over each control volume RBF interpolation achieve higher order accuracy. Two vortex-dominated viscous flows, NACA 0015 stationary wing at subsonic Mach number 0012 hovering rotor transonic tip speed,...
The aerodynamic performance of two open fan configurations is investigated and compared using Computational Fluid Dynamics analysis. Two systems based on NACA0012 NACA64-212 platforms are investigated, where the first modeled at three different rotational speeds second blade twists. Aerodynamic characteristics hover evaluated for both fans over a range collective angles. Numerical simulations indicate that chord length has significant impact formation laminar turbulent boundary layers...
In this study, a four-bladed HVAB rotor with cone and lag effects in hover is numerically investigated using an unstructured grid CFD solver. The integrated performance, intricate flow field on surfaces, trailing tip vortices the downwash are hybrid RANS-LES method. An innovative blending function utilized to merge near-wall RANS region off-wall LES current simulations. Grid sensitivity studies conducted assess impact of surface volume resolutions prediction performance field. Computed...
The flow inside turbo engines presents fully three-dimensional, unsteady, and complex viscous features such as secondary flows, boundary layer transitions, and/or separations. Accurate prediction of these phenomena is essential in the design analysis aero-thermal performance structural strength modern engines. In this study, a hybrid modeling strategy presented to simulate flows two turbine vanes: low-pressure/high-speed Pak-B high-pressure/high-speed VKI LS89. A wall adaptive local...
The structural dynamics and response of a two-bladed downwind wind turbine configuration using tilt control concept is examined based on Computational Structural Dynamics (CSD) analysis.Nacelle angles 5, 20, 35, 50 65 degrees are investigated varying speeds in order to achieve the same rated power output.Yaw 30, 40, 60 with purpose comparing loads displacements between two methods.The computed load effects reveal that tower top base shear forces reduced significantly nacelle compared yaw...