MW Energy Deposition for Aerodynamic Application

Kolesnichenko, Yuri; Brovkin, Vadim; Lashkov, V. A.; Mashek, I. Ch.

doi:10.2514/6.2003-361

Cited by 21 publications

(10 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Supersonic flow control by laser and MW discharge energy deposition has been investigated for many years (Miles 2000;Kolesnichenko et al 2001Kolesnichenko et al , 2003Yan et al June 2007;Knight et al 2009;Anderson and Knight 2011;Golbabaei Asl and Knight 2014). In particular, effects of destroying and modification of the bow shock wave can be used to control the flowfield around super-and hypersonic aircrafts and to reduce the drag.…”

Section: Introductionmentioning

confidence: 99%

Microwave discharge initiated by double laser spark in a supersonic airflow

et al. 2015

View full text Add to dashboard Cite

In this paper, we report the results of an experimental study of microwave (MW) discharge in the supersonic flow initiated by the laser spark and numerical simulation of multiple laser spark shockwave structures in airflow. The MW discharge initiation has been produced by single and double laser sparks. By using different spatial and temporal configuration of laser sparks in supersonic flow, we demonstrate the feasibility of an MW breakdown threshold decrease and control over shape and location of MW plasma. Calculation of laser spark shock wave structures shows good agreement with experimental shadow photographs both in the front shock wave diameter and its internal structure.

show abstract

Section: Introductionmentioning

confidence: 99%

Microwave discharge initiated by double laser spark in a supersonic airflow

et al. 2015

View full text Add to dashboard Cite

show abstract

“…5. Kolesnichenko et al ( , 2004 Kolesnichenko et al [34,[62][63][64][65][66][67] examined the effect of a microwave filament discharge on the aerodynamic drag of blunt bodies at M 1 1:7-2:1 in air, argon, carbon dioxide, and nitrogen. Typical peak microwave power was 220 kW at a maximum pulse duration of 2 s. Detailed spectral measurements of the plasma generated by the microwave pulse were performed and analyzed using a kinetic model.…”

Section: Exton Et Al (2001)mentioning

confidence: 99%

Survey of Aerodynamic Drag Reduction at High Speed by Energy Deposition

Knight

2008

Journal of Propulsion and Power

230

View full text Add to dashboard Cite

A selected survey of aerodynamic drag reduction at high speed is presented. The dimensionless governing parameters are described for energy deposition in an ideal gas. The types of energy deposition are divided into two categories. First, energy deposition in a uniform supersonic flow is discussed. Second, energy deposition upstream of a simple aerodynamic body is examined. Both steady and unsteady (pulsed) energy deposition are examined for both categories, as well as the conditions for the formation of shock waves and recirculation regions. The capability of energy deposition to reduce drag is demonstrated experimentally. Areas for future research are briefly discussed. Nomenclature A = cross-sectional area C D = drag coefficient c p = specific heat at constant pressure D = diameter of body d = diameter of filament G,G = spatial distribution functions for energy deposition I = impulse L = streamwise length ' = characteristic length M = freestream Mach number _ m = mass flow rate P = power p = pressure Q = energy added per unit volume per time Q o = magnitude of energy deposition (energy per unit volume per time) Q T = energy deposited in V in time interval e q = energy added per unit mass per time q o = magnitude of energy deposition (energy per unit mass per time) q T = energy per mass deposited in V in time interval e R = gas constant for air T = temperature T = temporal distribution function for energy deposition U = freestream velocity V = volume v = velocity = f = 1 = ratio of specific heats E f = energy added e , i , L = dimensionless time scales ", " 0 = energy deposition parameters = efficiency of energy deposition = density $ = ratio of energy added to energy required to choke the flow = dimensionless time parameter e = duration of energy pulse Subscripts f = filament 1 = freestream I. Overview I N RECENT years, there has been intense activity in developing a fundamental understanding and practical applications of flow control at high speed using energy deposition. This interest is reflected in numerous conferences and workshops, including the Weakly Ionized Gas Workshops [1-8], the St. Petersburg Workshops [9-12], and the Institute for High Temperatures Workshops [13][14][15][16][17][18][19]. The scope of this research is broad. It encompasses a wide variety of energy deposition techniques (e.g., plasma arcs, laser pulse, microwave, electron beam, glow discharge, etc.) and a wide range of applications (e.g., drag reduction, lift and moment enhancement, improved combustion and mixing, modification of shock structure, etc.).The objective of this paper is to provide a selective survey of research on aerodynamic drag reduction at high speed using energy deposition. The research is reviewed principally from the viewpoint of ideal gas dynamics to elucidate the thermal effects of energy deposition on supersonic flow. In general, nonideal gas effects are not considered (except insofar as they naturally occur in the experiments cited herein) and are the topic of a future survey.The remainder of this paper is d...

show abstract

“…Among different suggestions, an interesting idea directed toward this field is the possibility of reducing the aerodynamic drag and heating of a hypersonic vehicle by adding energy to the air ahead of it. This active control of the flowfield was suggested by several authors, with different methods for its accomplishment, in which theoretical and experimental reports present the plasma generation by plasma torch [1,2], electric arcs [3,4], surface electrical discharge [5], lasers [6][7][8][9][10], and microwaves [11,12]. The use of a focused laser beam is an attractive solution to attain this goal [13,14].…”

Section: Introductionmentioning

confidence: 99%

Bow Shock Wave Mitigation by Laser-Plasma Energy Addition in Hypersonic Flow

Oliveira

Minucci²,

Myrabo³

et al. 2008

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

Experimental results of bow shock wave mitigation by laser-plasma energy addition in a low-density Mach 7 hypersonic flow conducted in a shock tunnel are presented. A high-power pulsed CO 2 laser operating with 7 J of energy and 30 MW of peak power was used to generate the plasma ahead of a hemispherical model installed in the tunnel test section. The schlieren technique was used to visualize the time evolution of energy addition to the flow by laser-induced plasma and the interaction between this disturbed region and the inherent bow shock formed on the model by hypersonic flow. A complete mitigation of the bow shock profile under action of the energy addition was observed. The impact pressure on the hemispherical model measured at the stagnation point reveals the correlation between the schlieren images and the pressure reduction.

show abstract

MW Energy Deposition for Aerodynamic Application

Cited by 21 publications

References 0 publications

Microwave discharge initiated by double laser spark in a supersonic airflow

Microwave discharge initiated by double laser spark in a supersonic airflow

Survey of Aerodynamic Drag Reduction at High Speed by Energy Deposition

Bow Shock Wave Mitigation by Laser-Plasma Energy Addition in Hypersonic Flow

Contact Info

Product

Resources

About