On computational simulations of dynamic stall and its three-dimensional nature
In this paper, we investigate the three-dimensional nature of dynamic stall. Conducting the
investigation, the flow around a harmonically pitching National Advisory Committee for …
investigation, the flow around a harmonically pitching National Advisory Committee for …
Airfoil aerodynamics in ground effect for wide range of angles of attack
The aerodynamics and flow physics of a NACA 4412 airfoil in ground effect for a wide range
of angles of attack from− 4 to 20 deg are investigated by numerical simulations. The …
of angles of attack from− 4 to 20 deg are investigated by numerical simulations. The …
Numerical investigation of flows around an axisymmetric body of revolution by using Reynolds-stress model based hybrid Reynolds-averaged Navier–Stokes/large …
Flows around an axisymmetric body of revolution at a zero yaw angle were studied using a
hybrid Reynolds-averaged Navier–Stokes (RANS)/large eddy simulation (LES) approach …
hybrid Reynolds-averaged Navier–Stokes (RANS)/large eddy simulation (LES) approach …
Adaptive control method for morphing trailing-edge wing based on deep supervision network and reinforcement learning
J Dai, P Liu, C Kong, L Pan, J Si - Aerospace Science and Technology, 2024 - Elsevier
The morphing trailing-edge wing can adaptively change its shape according to the different
flight conditions, improving cruising efficiency. The control of the morphing trailing edge is a …
flight conditions, improving cruising efficiency. The control of the morphing trailing edge is a …
Data augmented prediction of Reynolds stresses for flows around an axisymmetric body of revolution
This work presents a data-driven approach to improve the predictive accuracy of the
Reynolds stresses for flows over an axisymmetric body of revolution. Sparse experimental …
Reynolds stresses for flows over an axisymmetric body of revolution. Sparse experimental …
Integrated computational/experimental approach to unmanned combat air vehicle stability and control estimation
RM Cummings, A Schütte - Journal of Aircraft, 2012 - arc.aiaa.org
M= Mach number, V= am= pitch moment, N mn= yaw moment, N mp= pressure, N= m2 q=
dynamic pressure, N= m2, V2= 2 S= wing reference area, m2 s= wing half-span, 0.769 m V …
dynamic pressure, N= m2, V2= 2 S= wing reference area, m2 s= wing half-span, 0.769 m V …
Numerical simulation of inlet buzz
M Abedi, R Askari, MR Soltani - Aerospace Science and Technology, 2020 - Elsevier
Comprehensive numerical analyses are conducted to simulate and capture “Buzz”
phenomenon in a supersonic mixed compression air inlet. The buzz is an unsteady self …
phenomenon in a supersonic mixed compression air inlet. The buzz is an unsteady self …
Feasibility of employing the restarting process to evaluate the self-starting ability for hypersonic inlets
W **e, Y **, Y Ge, S Yang, C Zeng, S Guo - Aerospace Science and …, 2020 - Elsevier
Accurate evaluation of hypersonic inlet self-starting performance is very crucial for the stable
and efficient operation of scramjet engines. However, few ground hypersonic wind tunnels …
and efficient operation of scramjet engines. However, few ground hypersonic wind tunnels …
IDDES method based on differential Reynolds-stress model and its application in bluff body turbulent flows
A general construction approach for a class of detached-eddy simulation (DES) methods
with the turbulent length-scale equation is presented in this study. It supports the rationality …
with the turbulent length-scale equation is presented in this study. It supports the rationality …
Dynamic lift characteristics of nonslender delta wing in large-amplitude-pitching
The unsteady aerodynamic characteristics of a 50° sweep delta wing performing pitching
oscillations at angle of attack between 0° and 60° were tested in a water channel facility …
oscillations at angle of attack between 0° and 60° were tested in a water channel facility …