Mach 10 Bow-Shock Unsteadiness Modeled by Linear Combination of Two Mechanisms [0.03%]
一种机制的线性组合模拟马赫数10激波相关的非定常现象
R Jeffrey Balla
R Jeffrey Balla
This paper presents mechanisms to explain, as well as mathematics to model, time-averaged spatially resolved amplitude observations of number density and number density unsteadiness in a Mach 10 flow as it transitions from the freestream, t...
Marlyn Y Andino,John C Lin,Seele Roman et al.
Marlyn Y Andino et al.
Active flow control (AFC) subscale experiments were conducted at the Lucas Wind Tunnel of the California Institute of Technology. Tests were performed on a generic vertical tail model at low speeds. Fluidic oscillators were used at the trai...
Influence of a Backward-Facing Step on Swept-Wing Boundary-Layer Transition [0.03%]
后向步对扫掠机翼边界层过渡的影响
Jenna L Eppink,Richard W Wlezien,Rudolph A King et al.
Jenna L Eppink et al.
Experimental measurements were performed on a swept flat-plate model with an airfoil leading edge and imposed chordwise pressure gradient to determine the effects of a backward-facing step on transition in a low-speed stationary crossflow-d...
Wall-Modeled Large-Eddy Simulation of a High Reynolds Number Separating and Reattaching Flow [0.03%]
大雷诺数分离回流的壁模LES模拟研究
George Ilhwan Park
George Ilhwan Park
The performance of two wall models based on Reynolds-averaged Navier-Stokes is compared in large-eddy simulation of a high Reynolds number separating and reattaching flow over the NASA wall-mounted hump. Wall modeling significantly improves...
Volterra Kernels Assessment via Time-Delay Neural Networks for Nonlinear Unsteady Aerodynamic Loading Identification [0.03%]
基于时延神经网络的非线性非定常气动载荷 Volterra 核评估
Natália C G de Paula,Flávio D Marques,Walter A Silva
Natália C G de Paula
Reduced-order modeling using the Volterra series approach has been successfully applied in the past decades to weakly nonlinear aerodynamic and aeroelastic systems. However, aspects regarding the identification of the kernels associated wit...
Effects of Sweeping Jet Actuator Parameters on Flow Separation Control [0.03%]
扫掠喷流激励器参数对分离流动控制的影响研究
Mehti Koklu
Mehti Koklu
A parametric experimental study was performed with sweeping jet actuators (fluidic oscillators) to determine their effectiveness in controlling flow separation on an adverse pressure gradient ramp. Actuator parameters that were investigated...
Mehti Koklu
Mehti Koklu
A parametric experimental study was performed with sweeping jet actuators (fluidic oscillators) to determine their effectiveness in controlling flow separation on an adverse pressure gradient ramp. Actuator parameters that were investigated...
Azimuthal Variation of Instabilities Generated on a Flared Cone by Laser Perturbations [0.03%]
激光扰动下喇叭形圆锥体表面不稳定性发展的方位角依赖性
Amanda Chou,Steven P Schneider
Amanda Chou
To study the azimuthal development of boundary-layer instabilities, a controlled, laser-generated perturbation was created in the freestream of the Boeing/U.S. Air Force Office of Scientific Research Mach 6 Quiet Tunnel. The freestream pert...
Interaction of a Backward-Facing Step and Crossflow Instabilities in Boundary-Layer Transition [0.03%]
回流步和边界层转型中交变流动不稳定的相互作用
Jenna L Eppink,Richard W Wlezien,Rudolph A King et al.
Jenna L Eppink et al.
A swept flat plate model with an imposed pressure gradient was experimentally investigated in a low-speed flow to determine the effect of a backward-facing step on transition in a stationary crossflow-dominated flow. Detailed hotwire measur...
Progress Toward Accurate Measurement of Dielectric Barrier Discharge Plasma Actuator Power [0.03%]
向精确测量介质阻挡放电等离子体作动器功率进展
David E Ashpis,Matthew C Laun,Elmer L Griebeler
David E Ashpis
The accurate measurement of power consumption by dielectric barrier discharge plasma actuators is a challenge due to the characteristics of the actuator current signal. Microdischarges generate high-amplitude, high-frequency current spike t...