Numerical Simulation of Wake Deflection Control around NACA0012 Airfoil Using Active Morphing Flaps

نویسندگان
چکیده

برای دانلود باید عضویت طلایی داشته باشید

برای دانلود متن کامل این مقاله و بیش از 32 میلیون مقاله دیگر ابتدا ثبت نام کنید

اگر عضو سایت هستید لطفا وارد حساب کاربری خود شوید

منابع مشابه

experimental investigation of flow turbulence effects on the flow wake parameters around a naca0012 airfoil

in this paper, inflow turbulence effects on the flow wake parameters around a naca0012 airfoil at zero incidence angle and reynolds number of 38,700 were investigated. various turbulence promoter networks were used to achieve turbulence intensity of 5% and 6%. experiments have been conducted for three different turbulence intensities in which mean velocity parameters, turbulence intensity, freq...

متن کامل

Numerical Study of Blowing and Suction Control Mechanism on NACA0012 Airfoil

A jet with a width of 2.5% the chord length is placed on a NACA0012 airfoil’s upper surface simulating the blowing and suction control under Re = 5 × 105 and angle-of-attack 18-deg conditions. Nearly 300 numerical simulations are conducted over a range of parameters (jet location, amplitude, and angle). The physical mechanisms that govern suction and blowing flow control are determined and anal...

متن کامل

experimental investigation of active flow control for changing stall angle of a naca0012 airfoil, using plasma-actuator

active flow control has great importance in design of flying objects in general and control flaps in particular. using dielectric barrier discharge as plasma actuators over control flaps can cause a change in position of separation point or can eliminate it. this new flow control device produces a body force that causes generating a micro wall jet. the present study aims to investigate experime...

متن کامل

Aerodynamics of a Morphing Airfoil

The purpose of this research is to develop a MATLAB model which can calculate the aerodynamics, such as lift, drag, and pressure, on an airfoil as it changes shape. This model needs to be computationally efficient and should have reasonable accuracy. A constant strength doublet panel code, which takes thickness and camber distribution as inputs, is used to model the aerodynamics. This code has ...

متن کامل

Numerical Simulation of Flow Past Oscillating Airfoil Using Oscillation of Flow Boundary Condition

The present study is devoted to an approximate modeling for numerical simulation of flows past oscillating airfoils. In this study, it is shown that the harmonic oscillating objects can be studied by simple numerical codes that are not able to solve moving grids. Instead of using moving grid for the simulation of flowfield around an oscillating airfoil, this unsteady flow is solved on a fixed g...

متن کامل

ذخیره در منابع من


  با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید

ژورنال

عنوان ژورنال: Journal of Flow Control, Measurement & Visualization

سال: 2020

ISSN: 2329-3322,2329-3330

DOI: 10.4236/jfcmv.2020.83007