This study presents an innovative implicit–explicit time-stepping algorithm based on a first-order temporal accuracy method, addressing challenges in simulating all-regimes of fluid flows. The algorithm's primary focus is mitigating stiffness inherent the density-based “Roe” pivotal finite volume approaches employing unstructured meshes. objective to comprehensively evaluate method's efficiency and robustness, contrasting it with explicit fourth-order Runge–Kutta method. evaluation...

The vital role of the numerical scheme is becoming increasingly critical as use computational fluid dynamics grows. To address unfavorable effects experienced in low-speed flows when using AUSM+M (Improved Advection Upstream Splitting Method), present paper presents an improved approach known Modified-AUSM+M (M-AUSM+M). This novel method offers enhanced reliability simulating low-Mach number flows, effectively mitigating challenges associated with symptoms encountered original scheme....

This paper introduces a novel platform that integrates three preconditioning matrices based on conservative variables: the Turkel, Choi–Merkle and Onur matrices. The aims to compare these in terms of accuracy robustness by investigating their performance solving distinct challenging high-gradient laminar flow problems: (i) Bi-Plane NACA0012 airfoil, (ii) lid-driven square cavity (iii) planar T-junction. These problems serve as new test cases accurately determine abilities are applied...

In the present study, effects of wing fence on tip vortices and control surfaces located at in a flying aircraft have been investigated using numerical method. For size fences, average dimensions extracted from different angles attack are used. The basic determining parameter is rolling torque coefficient, which tried to be shown by employing parametric study flow behavior situations placement. These measured due presence split drag rudder system. this fences were installed three heights...

This paper introduces NAUSM+M+AUFS (New Improved Advection Upstream Splitting Method Plus Artificially Flux Vector Splitting), a novel hybrid computational scheme for simulating compressible flows on triangular grids. The AUSM+M (Improved Method) method is enhanced through two key modifications to boost numerical stability and robustness in high Mach number hypersonic flows. first modification redefines the interfacial sound velocity, reducing shock anomalies improving shock-capturing by...

In this paper, the effects of twist angle variation on aerodynamic coefficients and flow field wing with smarting approach are studied using numerical simulation. The simulation was performed incompressible Reynolds-Averaged Navier-Stokes (RANS) equations based two-equation k-ω Shear Stress Transport (SST) turbulent model for speed 30 m/s a Reynolds number 69000. Investigations have been carried out several angles at specific range attack. applied is type geometric (wash-out), which linearly...

This paper introduces a novel hybrid numerical method, SAUSM, designed for accurate and robust simulation of compressible flows governed by the Euler equations. While AUSM[Formula: see text] scheme provides proper resolution smooth flow features, it is susceptible to anomalies, particularly carbuncle phenomenon near strong shock discontinuities. Conversely, AUFS offers inherent stability in capturing shocks; however, lacks accuracy regions. The proposed SAUSM method combines through an...

Sinusoidal leading-edge wings have shown a high performance after the stall region. In this study, role of smart flaps in aerodynamics smooth and sinusoidal at low Reynolds numbers 29,000, 40,000 58,000 is investigated. Four with NACA 63 4 -021 profile are firstly designed then manufactured by 3 D printer. Beam bending equation used to determine flap chord deflection. Next, wind tunnel tests carried out measure lift drag forces proposed for wide range angles attack, from zero 36 degrees....

This paper covers the topic of interaction process between a detonation wave and cloud inert particles.A computer code based on numerical method Flux Corrected Transport algorithm was developed to solve Euler equations for inviscid flow.The chemical reaction is modeled with one-step Arrhenius chemistry, particle phase in Lagrangian frame reference.Simulation results illustrate that could be suppressed by particle, if parameters meet some critical conditions.

Scientists have been improving the aerodynamic performance of flapping micro aerial vehicles by drawing inspiration from birds and insect flight. In this research study, first, mechanism black-headed gull is designed then it constructed in order to investigate effects wing bending deflection on performance. Thrust generation, power consumption loading are considered as parameters. Three wings representing different underlying structures, namely flexible membrane, rigid membrane airfoil,...

In the present study, a novel FD_LBM hybrid numerical method with total variation diminishing (TVD) characteristics is proposed to solve famous problems of MagnetoHydroDynamics (MHD) and natural convection in closed cavity. Here, momentum energy equations are carried out via lattice Boltzmann (LBM) FD techniques, respectively. To enhance stability performance finite difference scheme for higher Ra numbers, two renowned Superbee Minmod flux limiter functions were used. The results heat...

Wing smarting and eliminating conventional control surfaces are fundamental parameters for improving aircraft aerodynamic performance in future aviation. Twist is a well-known tool that, along with the development of morphing technology, can play crucial role controlling next-generation aircraft. However, wing twisting approach requires many studies, particularly at high aft-swept angle; this more noticeable flying configuration. In paper, strategy based on twist has been evaluated...

Many developments in aerospace science have originated from nature. One of these has been obtained through inspirations flying locomotion. The aim this study is to simulate the flapping mechanism black-headed gull forward flight. wing characterized entirely by complex dihedral, dividing into two distinct parts. Hence, a with different bending deflection angles constructed and compared primitive mechanism. Firstly, parametric studies are conducted assess role frequency, velocity angle on...

In this research, viscous, laminar and steady flow around symmetric non-symmetric airfoils is simulated at Low Reynolds Number (LRN).Navier-Stokes (N-S) equations are discretized by Finite Volume Method (FVM) solved the SIMPLE algorithm in an open source software, namely OpenFOAM.The main objective of paper introduction thermal camber phenomenon.This phenomenon used to improve aerodynamic performance.Hence, a airfoil, like NACA0012, with compared physical camber, including NACA2412 NACA4412,...

This paper opens a new horizon on the sim- ulation of sloshing phenomena. One most popular Finite Volume methods called VOF (Volume Of Fluid) method is used for tracking flow in containers. The algorithm tested different fluid elevations, physical conditions road curves and liquid properties. then validated against an analytical another numerical solution. These comparisons show that can effectively solve problem fluids variety geomet- rical conditions. keyword: Pressure-based Method, VOF,...