Numerical investigation of the compressible flow past a wavy cylinder was carried out using large-eddy simulation for free-stream Mach number M ∞ = 0.75 and Reynolds based on mean diameter Re 2 × 10 5 . The corresponding circular also calculated comparison validation against experimental data. Various fundamental mechanisms dictating intricate phenomena, including drag reduction fluctuating force suppression, shock shocklet elimination, three-dimensional separation separated shear-layer...

Numerical investigation of the compressible flow past an 18% thick circular-arc aerofoil was carried out using detached-eddy simulation for a free-stream Mach number M ∞ = 0.76 and Reynolds Re 1.1 × 10 7 . Results have been validated carefully against experimental data. Various fundamental mechanisms dictating intricate phenomena, including moving shock wave behaviours, turbulent boundary layer characteristics, kinematics coherent structures dynamical processes in evolution, studied...

This work presents a simulation of infectious droplet dispersion in civil aircraft cabin with the Euler-Lagrangian method. The influence different rates air supply on airflow field, dispersion, and concentration distribution droplets are analysed. results show have significant impact filed. area vortex circulation region is reduced. Total mass basically reaches stability after infector exhales for 120 seconds. total 3.56×10-12kg 6.9 L per second person respectively decreased by 4.21% 22.75%...

The compressible flows past a wavy-axis square cylinder are numerically carried out by means of the large-eddy simulation technique for two different free-stream Mach numbers (M∞=0.71 and 0.85), which less than critical number Mcr (≈0.9). Reynolds based on side-length is chosen as 4×105. For comparison, around corresponding normal also calculated. control effects mechanisms systematically analyzed. Comparing with M∞=0.71 0.85, about 23.5% 8.1% drag reductions acquired, respectively,...

Rocket-sleds belong to a category of large-scale test platforms running on the ground which are mainly used for launching tests weapon equipment and performance airborne equipment. In present study, dynamic grid method was simulate process an axisymmetric slender rocket-sled (ASRS) reversed waverider (RWRRS). The aerodynamic characteristics were studied ability control shockwave with effect confirmed. addition reducing oscillation, RWRRS also able increase lift reduce drag. By means power...

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The interaction of shock wave and turbulence for transonic flow over a circular cylinder is investigated using detached-eddy simulation (DES). Several typical cases are calculated free-stream Mach number M ∞ from 0.85 to 0.95, the physical mechanisms relevant discussed. Results show that there exist two states. One unsteady state with moving waves interacting turbulent < 0.9 approximately, other quasi-steady stationary shocks standing wake > 0.9, suppressing vortex shedding cylinder....

The calculation of a cockpit’s transient thermal load is important for determining the capacity cockpit environmental control system, ensuring safety electronic equipment and increasing health comfort occupants. According to structural parameters sightseeing airship, physical model established. turbulence method are selected verified. within full flight envelope, loads at different times day, under free-flow velocities obtained based on Computational Fluid Dynamics (CFD) method. during...

The separated flow past a 6:1:1 spheroid is numerically investigated by means of the scale-adaptive simulation technique. Reynolds number based on free-stream velocity and diameter at middle-section located in subcritical regime, i.e., Re = 3900. In comparison with circular cylinder same number, about 35% drag reduction acquired spheroid, fluctuations lift are suppressed effectively. According to detailed comparison, satisfactory suppression fluctuating force obtained closely associated...

Pulsatile non-Newtonian fluid flow was simulated in an artery bifurcation model, with three different inlet waveform shapes and identical mean velocity steady-state condition, to quantify the impact of on hemodynamics such as patterns, wall shear stress, oscillatory index during a cardiac cycle. It found that degree separation is insensitive changes shape. There remarkable similarity position magnitude maximum stress at peak systole time-averaged for all examined cases. The distributions are...

A supersonic flow past a hemispherical nose with an opposing jet placed on its axis has been investigated using large eddy simulation. We find that the behaviors depend mainly total pressure ratio and can be classified into three typical regimes of unstable, stable transition. The unstable regime is characterized by oscillatory bow shock multi-jet-cell structure steady single cell. transition lies between ones complex evolution. Turbulence statistics are further analyzed to reveal relevant...

The compressible turbulent flows past wavy-axis cylinder have been studied numerically using the large-eddy simulation technique. free-stream Mach number and Reynolds based on diameter are 0.75 2 × 105, respectively. To investigate effects of angle attack force behaviors wake characteristics, several angles adopted, i.e., α = 0°, 15°, 30°, 45°, 60°, 75° 90°. Results show that there two different behaviors, as well characteristics around critical about 45°. One is effective drag reduction...

Rocket sleds belong to a category of large-scale test platforms running on the ground. The applications can be found in many fields, such as aerospace engineering, conventional weapons, and civil high-tech products. In present work, shock-wave/rail-fasteners interaction is investigated numerically when rocket sled supersonic flow conditions. Two typical models are considered, i.e., an anti-D shaped version axisymmetric slender-body variant. dynamics for Mach number 2 have been simulated...

A vortex ring impinging on a three-dimensional bump is studied using large eddy simulation for Reynolds number Re = 4 × 104 based the initial translation speed and diameter of ring. The effects height vortical flow phenomena underlying physical mechanisms are investigated. Based analysis evolution structures, two typical kinds i.e., wrapping vortices hair-pin vortices, identified play an important role in state evolution. circulation primary reasonably elucidates some phases Furthermore,...

Large-eddy simulation (LES) of the Navier–Stokes equations is carried out to investigate supersonic turbulent boundary layer (STBL) developing over a flat plate at free-stream Mach number M∞=2.0 and Reynolds Reδ≈ 13 500. The seventh-order weighted essentially non-oscillatory (WENO-7) scheme adopted ensure calculation accuracy. To demonstrate credibility proposed improvements, posteriori test conducted. Other LES-like methods are also for comparison. validation results show that WENO-LES can...