Navier-Stokes analysis of supersonic flow with local energy deposition

Левин, В. А.; Afonina, N. E.; Gromov, V. G.

doi:10.2514/6.1999-4967

Cited by 9 publications

(5 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Besides experimental investigations, numerical efforts have also been done to examine the effect of energy deposition in compressible flow. Georgievsky and Levin et al [288][289][290][291] have done early numerical efforts by applying Euler equations to predict a reduction in heat and drag on blunt and sharp bodies. Some researchers carried out the numerical simulation by applying an unsteady Euler equation to observe the influence of laser pulse on shock wave mitigation.…”

Section: Energy Deposition Methodsmentioning

confidence: 99%

Review of wave drag reduction techniques: Advances in active, passive, and hybrid flow control

Rashid

Nawaz

Maqsood

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

Typical challenges of supersonic flight include wave drag, acoustic signature, and aerodynamic heating due to the formation of shock waves ahead of the vehicle. Efforts in the form of sleek aerodynamic designs, better propulsion systems, and the implementation of passive and active techniques are generally adopted to achieve a weaker shock wave system. Shock reduction can improve flight range, reduce fuel consumption, and provide thermal protection of the forebody region. This paper briefly reviews shock reduction techniques, including passive, active, and hybrid flow control. Airfoil shape optimization, mechanical spike, and forebody cavities are studied as passive flow control approaches. For active flow control, developments in the area of opposing jets and energy deposition are explored. The combination of active and passive flow control and the hybrid flow techniques are discussed in the end. The discussions include the principle of operation, physics of fluid behavior, and overall contribution to flight stability characteristics. The implications in the usage of these technologies, along with potential gaps, are also identified. This comprehensive review can serve as the basis for contemporary solutions to realize sustainable supersonic travel for the aviation industry.

show abstract

Section: Energy Deposition Methodsmentioning

confidence: 99%

Review of wave drag reduction techniques: Advances in active, passive, and hybrid flow control

Rashid

Nawaz

Maqsood

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…0, the pulsed energy deposition acts like a quasi-steady source of energy upstream of the flow. It is well known [30,40,46,47,57] that steady energy deposition upstream of a blunt body reduces the drag due to the reduction in u 2 with heat addition.…”

Section: Georgievskii and Levin (2003)mentioning

confidence: 99%

Survey of Aerodynamic Drag Reduction at High Speed by Energy Deposition

Knight

2008

Journal of Propulsion and Power

232

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

“…The flowfield calculation at every iiine step is perfomled by the Gaiiss-Seidel line relaxation numerical technique. Based on this approach, the numerical code was developed by V. G. Gromov with colleagues [8,9] at the IM/MSU for the MS platform and used for several research projects. Note that this approach is similar to the approach employed in the NASA numerical code VULCAN.…”

Section: 2mentioning

confidence: 99%

Shock waves mitigation at blunt bodies using needles and shells against a supersonic flow

Gilinsky

Blankson

Сахаров

et al. 2001

37th Joint Propulsion Conference and Exhibit

View full text Add to dashboard Cite

The paper contains some experimental and numerical simulation test results on cylindrical blunt body drag reduction using thin spikes or shell mounted in front of a body against a supersonic flow. Experimental tests were conducted using the Aeromechanics and Gas Dynamics Laboratory facilities at the Institute of Mechanics of Moscow State University (IMMSU). Numerical simulations utilizing NASA and IM/MSU codes were conducted at the Hampton University Fluid Mechanics and Acoustics Laboratory. The main purpose of this research is to examine the efficiency of application of multiple spikes for drag reduction and flow stability at the front of a blunt body in different flight conditions, i.e. Mach number, angle of attack, etc. The principal conclusions of these test results are: multiple spikeheedle application leads to decrease of drag reduction benefits by comparison with the case of one central mounted needle at the front of a blunt bodyi but increase lift benefits.

show abstract

Navier-Stokes analysis of supersonic flow with local energy deposition

Cited by 9 publications

References 0 publications

Review of wave drag reduction techniques: Advances in active, passive, and hybrid flow control

Review of wave drag reduction techniques: Advances in active, passive, and hybrid flow control

Survey of Aerodynamic Drag Reduction at High Speed by Energy Deposition

Shock waves mitigation at blunt bodies using needles and shells against a supersonic flow

Contact Info

Product

Resources

About