Esmaeil Esmaeilifar- Doctor of Engineering
- Postdoctoral Researcher at Gyeongsang National University
Esmaeil Esmaeilifar
- Doctor of Engineering
- Postdoctoral Researcher at Gyeongsang National University
Quantum Computing for Fluid Flow Simulation
About
16
Publications
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169
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Introduction
Proficient in Computational Fluid Dynamics, I hold a Ph.D. in Aerospace Engineering with a strong publication record and over 150 citations. I specialize in developing scientific solvers and models for Multiphysics simulations. My research interests extend beyond traditional CFD, as I am actively exploring the potential of quantum computing for solving complex problems in fluid dynamics.
Current institution
Education
March 2019 - August 2023
September 2012 - September 2015
September 2006 - May 2012
Publications
Publications (16)
Rotorcraft rotor-fuselage-intake aerodynamics and icing present unique challenges associated with rotor-wake dynamics and the interaction of rotor wake with the fuselage and the intake. The effects of the rotor wake are dominant in low forward flight, and performing high-fidelity simulations of the rotor-fuselage-intake simultaneously is expensive....
For understanding many real-world problems involving rarefied hypersonic, micro-, and nanoscale gas flows, the primary method may be the direct simulation Monte Carlo (DSMC). However, its computational cost is prohibitive in comparison with the Navier–Stokes–Fourier (NSF) solvers, eclipsing the advantages it provides, especially for situations wher...
Recent advances in quantum hardware and quantum computing algorithms promise significant breakthroughs in computational capabilities. Quantum computers can achieve exponential improvements in speed vs classical computers by employing principles of quantum mechanics like superposition and entanglement. However, designing quantum algorithms to solve...
Conventional anti-icing computational solvers calculate the convective heat transfer coefficient using a homogeneous thermal boundary condition, assuming a constant temperature across the surface. However, this approach can lead to inaccuracies in regions with significant temperature variations. To address this limitation, the present study propose...
The aircraft industry often uses computational methods to quantify ice accretion, investigate aerodynamic penalties, and conduct certification processes. The computational simulation of aircraft icing is computationally intensive owing to three consecutive runs of air, droplet, and ice accretion solvers. This study developed a parallel code using M...
Accurately predicting de-icing processes is essential to ensure the proper sizing and design of ice protection systems in aircraft icing. A unified framework was developed to simulate an unsteady electrothermal de-icing process, using an unsteady formulation to account for phase change and runback water. Two physically-motivated concepts were newly...
View Video Presentation: https://doi.org/10.2514/6.2022-0447.vid This study presents a three-dimensional computational model to compute glaze ice accretion on complex configurations. A unified analysis system of clean air, droplet impingement, and ice accretion—all of which are based on a single unstructured upwind finite volume framework—was used...
NVLM, CFD, Coupling, Helicopter aerodynamics, VPM
In this study, viscous, turbulent, and steady flow around an airfoil near the water surface has been simulated through a numerical method. In this simulation, Navier-Stokes equations have been solved using the finite volume method with a discretized second-order accuracy and PIMPLE algorithm. The Volume of Fraction (VOF) method has been employed to...
In this research, viscous, unsteady and turbulent fluid flow is simulated numerically around a pitching NACA0012 airfoil in the dynamic stall area. The Navier-Stokes equations are discretized based on the finite volume method and are solved by the PIMPLE algorithm in the open source software, namely OpenFOAM. The SST k - ω model is used as the turb...
ABSTRACT: In this research, viscous, laminar and steady flow around symmetric and non-symmetric airfoils is simulated at
Low Reynolds Number (LRN). Navier-Stokes (N-S) equations are discretized by Finite Volume Method (FVM) and are solved by
the SIMPLE algorithm in an open source software, namely OpenFOAM. The main objective of this paper is the in...
