CHARACTERISTICS OF FORE-BODY SEPARATE FLOW AT HIGH ANGLE OF ATTACK UNDER PLASMA CONTROL

2010 ◽  
Vol 24 (13) ◽  
pp. 1401-1404 ◽  
Author(s):  
JIANLEI WANG ◽  
HUAXING LI ◽  
FENG LIU ◽  
SHIJUN LUO
Keyword(s):  
Wind Tunnel ◽  
Separate Flow ◽  
Plasma Actuator ◽  
Apex Angle ◽  
Plasma Actuators ◽  
Aerodynamic Load ◽  
Pressure Measurements ◽  
High Angle ◽  
Asymmetric Force ◽  
High Angles Of Attack

A pair of plasma actuators with horseshoe shape is proposed for dynamic manipulation of forebody aerodynamic load at high angles of attack. Preliminary wind tunnel pressure measurements show that asymmetric force over a conical forebody with semi-apex angle 10° can be manipulated by activating the plasma actuator mounted on one side of the cone tip. Further work is suggested.

PLASMA FLOW CONTROL OVER FOREBODY AT HIGH ANGLES OF ATTACK

2010 ◽  
Vol 24 (13) ◽  
pp. 1405-1408 ◽  
Author(s):  
ZIJIE ZHAO ◽  
CHAO GAO ◽  
FENG LIU ◽  
SHIJUN LUO
Keyword(s):  
Wind Tunnel ◽  
Flow Control ◽  
Plasma Flow ◽  
Vortex Pair ◽  
Apex Angle ◽  
Plasma Actuators ◽  
Pressure Measurements ◽  
Asymmetric Vortex ◽  
Plasma Flow Control ◽  
High Angles Of Attack

Forward blowing from a pair of plasma actuators on the leeward surface and near the apex is used to switch the asymmetric vortex pair over a cone of semi-apex angle 10° at high angles of attack. Wind tunnel pressure measurements show that by appropriate design of the actuators and appropriate choice of the AC voltage and frequency, side forces and yawing moments of opposite signs can be obtained at a given angle of attack by activating one of the plasma actuators. Further work is suggested.

scholarly journals Wind Tunnel Testing of Plasma Actuator with Two Mesh Electrodes to Boundary Layer Control at High Angle of Attack

Sensors ◽  
2021 ◽  
Vol 21 (2) ◽  
pp. 363
Author(s):  
Ernest Gnapowski ◽  
Jarosław Pytka ◽  
Jerzy Józwik ◽  
Jan Laskowski ◽  
Joanna Michałowska
Keyword(s):  
Boundary Layer ◽  
Wind Tunnel ◽  
Experimental Research ◽  
Lift Coefficient ◽  
Angle Of Attack ◽  
Experimental Tests ◽  
Plasma Actuator ◽  
High Angle ◽  
Dbd Plasma ◽  
High Angle Of Attack

The manuscript presents experimental research carried out on the wing model with the SD 7003 profile. A plasma actuator with DBD (Dielectric Barrier Discharge) discharges was placed on the wing surface to control boundary layer. The experimental tests were carried out in the AeroLab wind tunnel where the forces acting on the wing during the tests were measured. The conducted experimental research concerns the analysis of the phenomena that take place on the surface of the wing with the DBD plasma actuator turned off and on. The plasma actuator used during the experimental tests has a different structure compared to the classic plasma actuator. The commonly tested plasma actuator uses solid/impermeable electrodes, while in the research, the plasma actuator uses a new type of electrodes, two mesh electrodes separated by an impermeable Kapton dielectric. The experimental research was carried out for the angle of attack α = 15° and several air velocities V = 5–15 m/s with a step of 5 m/s for the Reynolds number Re = 87,500–262,500. The critical angle of attack at which the SD 7003 profile has the maximum lift coefficient is about 11°; during the experimental research, the angle was 15°. Despite the high angle of attack, it was possible to increase the lift coefficient. The use of a plasma actuator with two mesh electrodes allowed to increase the lift by 5%, even at a high angle of attack. During experimental research used high voltage power supply for powering the DBD plasma actuator in the voltage range from 7.5 to 15 kV.

scholarly journals Closed loop control of aerodynamic load fluctuations on wind turbine airfoil using surface plasma actuators

2020 ◽  
Vol 53 (2) ◽  
pp. 12675-12681
Author(s):  
Dominique Nelson-Gruel ◽  
Pierrick Joseph ◽  
Alexis Paulh-Manssens ◽  
Annie Leroy ◽  
Sandrine Aubrun ◽  
...  
Keyword(s):  
Wind Turbine ◽  
Closed Loop ◽  
Plasma Actuators ◽  
Aerodynamic Load ◽  
Closed Loop Control ◽  
Surface Plasma ◽  
Loop Control ◽  
Wind Turbine Airfoil

Wind-tunnel investigation of a fighter model at high angles of attack

1992 ◽  
Vol 29 (6) ◽  
pp. 1091-1097 ◽  
Author(s):  
Sheshagiri K. Hebbar ◽  
David H. Leedy
Keyword(s):  
Wind Tunnel ◽  
High Angles Of Attack

scholarly journals Cable Suspension and Balance System with Low Support Interference and Vibration for Effective Wind Tunnel Tests

2021 ◽  
Author(s):  
Keum-Yong Park ◽  
Yeol-Hun Sung ◽  
Jae-Hung Han
Keyword(s):  
Wind Tunnel ◽  
Vibration Suppression ◽  
Aerodynamic Load ◽  
Test Model ◽  
Wind Tunnel Tests ◽  
Balance System ◽  
Motion Responses ◽  
Vibration Responses ◽  
Aerodynamic Interference ◽  
Support Interference

AbstractA cable-driven model support concept is suggested and implemented in this paper. In this case, it is a cable suspension and balance system (CSBS), which has the advantages of low support interference and reduced vibration responses for effective wind tunnel tests. This system is designed for both model motion control and aerodynamic load measurements. In the CSBS, the required position or the attitude of the test model is realized by eight motors, which adjust the length, velocity, and acceleration of the corresponding cables. Aerodynamic load measurements are accomplished by a cable balance consisting of eight load cells connected to the assigned cables. The motion responses and load measurement outputs were in good agreement with the reference data. The effectiveness of the CSBS against aerodynamic interference and vibration is experimentally demonstrated through comparative tests with a rear sting and a crescent sting support (CSS). The advantages of the CSBS are examined through several wind tunnel tests of a NACA0015 airfoil model. The cable support of the CSBS clearly showed less aerodynamic interference than the rear sting with a CSS, judging from the drag coefficient profile. Additionally, the CSBS showed excellent vibration suppression characteristics at all angles of attack.

Strakes Effects on Asymmetric Flow Over a Blunt-Nosed Slender Body at a High Angle of Attack

2018 ◽  
Vol 141 (6) ◽  
Author(s):  
Qihang Yuan ◽  
Yankui Wang ◽  
Zhongyang Qi
Keyword(s):  
Angle Of Attack ◽  
Slender Body ◽  
Axial Position ◽  
High Angle ◽  
Asymmetric Flow ◽  
High Angle Of Attack ◽  
Side Force ◽  
Asymmetric Vortices ◽  
High Angles Of Attack ◽  
Blunt Nose

In general speaking, the missiles execute flight at high angles of attack in order to enhance their maneuverability. However, the inevitable side-force, which is caused by the asymmetric flow over these kinds of traditional slender body configurations with blunt nose at a high attack angle, induces the yawing or rolling deviation and the missiles will lose their predicted trajectory consequently. This study examines and diminishes the side-force induced by the inevitable asymmetric flow around this traditional slender body configuration with blunt nose at a high angle of attack (AoA = 50 deg). On one hand, the flow over a fixed blunt-nosed slender body model with strakes mounted at an axial position of x/D = 1.6–2.7 is investigated experimentally at α = 50 deg (D is the diameter of the model). On the other hand, the wingspan of the strakes is varied to investigate its effect on the leeward flow over the model. The Reynolds number is set at ReD = 1.54 × 105 based on D and incoming upstream velocity. The results verify that the formation of asymmetric vortices is hindered by the existence of strakes, and the strake-induced vortices develop symmetrically and contribute to the reduction in side-force of the model. In addition, the increase in strake wingspan reduces asymmetric characteristics of the vortex around the model and causes a significant decrease in side-force in each section measured. The strake with the 0.1D wingspan can reduce the sectional side-force to 25% of that in the condition without strakes.

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