Sekimoto Satoshi

論文

Correction: Aerodynamic Optimization of Angular Airfoil for Micro-Scale Mars Airplane

Aerodynamic Optimization of Angular Airfoil for Micro-Scale Mars Airplane

Effect of pressure sensor arrangement on deep reinforcement learning-based feedback control of separated flow around aerofoils

Predetermined control of a leading-edge vortex on a pitching aerofoil

Spatiotemporal evolution of molar fraction in acoustic-resonance tube filled with He-Ar mixture

Revisiting acoustical gas-mixture separation

Flow Control around NACA0015 Airfoil Using a Dielectric Barrier Discharge Plasma Actuator over a Wide Range of the Reynolds Number

In-Flight Demonstration of Stall Improvement Using a Plasma Actuator for a Small Unmanned Aerial Vehicle

Dynamic Burst Actuation to Enhance the Flow Control Authority of Plasma Actuators

A high-fidelity body-force modeling approach for plasma-based flow control simulations

Computational Study of Wing-Tip Effect for Flow-Control Authority of Dielectric-Barrier-Discharge Plasma Actuator

Closed-Loop Flow Separation Control Using the Deep Q Network over Airfoil

Flow-control capability of electronic-substrate-sized power supply for a plasma actuator

Compact Nanosecond Pulsed Power Supply for Plasma Actuator on Unmanned Aerial Vehicle

Aerodynamic drag reduction of a simplified vehicle model by promoting flow separation using plasma actuator

Experimental Analysis of Closed-Loop Flow Control Around Airfoil Using DBD Plasma Actuator

Study on the Sensing Parameters toward Better Feed-back Control of Stall Separation with DBD Plasma Actuator

Burst-Mode Frequency Effects of Dielectric Barrier Discharge Plasma Actuator for Separation Control

共同研究・競争的資金等の研究課題

Demonstration and model construction for reduction of acoustical minor loss using micro fluid device

Control of Boundary-Layer Transition for Skin Friction Drag Reduction of Aircraft by Plasma Actuator

Establishment of flow control technique using transient aerodynamic force with a microdevice

Dynamic Flow Control of Model Aircraft with Electric Micro Device and the Flight Demonstration

Analysis of Flow Control Authority of DBD Plasma Actuator in Practical Use