Theoretical and experimental study of the possibility of reducing aerodynamic drag by employing plasma injection

Ganiev, Y. C.; Gordeev, V. P.; Krasilnikov, Arthur; Lagutin, V. I.; Otmennikov, V. N.; Панасенко, А. В.

doi:10.2514/6.1999-603

Cited by 20 publications

(10 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The jet temperature was proved in some studies to have no impact on the fore shock standoff distance [169] nor on drag [168]. Other studies [166,170] confirmed that increasing the jet total temperature yields more drag reduction which explains the relative superiority of plasma and high-temperature jets over conventional ones [166].…”

Section: Factors Controlling the Counterflow Effectivenessmentioning

confidence: 98%

“…This is attained by passing the gas through a high voltage electrode placed within the forebody. The pioneering proof-of-concept experimental work in this field was conducted by Gordeev and his research group [210][211][212]. The idea was based on augmenting the conventional opposing jet device with the favorable drag reduction features of electric discharge.…”

Section: Derivatives Of Opposing Jet Device 371 Opposing Plasma Jetsmentioning

confidence: 99%

“…This feature of plasma discharge (along with other energy discharge forms) will be discussed later in this survey. To date, the studies on opposing plasma jet have been exclusive to three research groups: Gordeev et al [166,170,210,213,214], Shang et al [152,215,216], and Fomin et al [217,218].…”

Section: Derivatives Of Opposing Jet Device 371 Opposing Plasma Jetsmentioning

confidence: 99%

See 2 more Smart Citations

Forebody shock control devices for drag and aero-heating reduction: A comprehensive survey with a practical perspective

Ahmed

Qin

2020

Progress in Aerospace Sciences

View full text Add to dashboard Cite

One key feature that distinguishes the flowfield around vehicles flying in supersonic and hypersonic regimes is the bow shock wave ahead of forebody. The severe drag and aeroheating impacting these vehicles can be significantly reduced if the bow shock wave ahead of the vehicles forebodies is controlled to yield weaker system of oblique shocks. Benefits of forebody shock control include increasing flight ranges, economizing fuel consumption, reducing dead weights, and thermally protecting forebody structure and onboard equipment. Forebody shock control that has been widely studied since the early 1900s is achievable in numerous techniques that vary according to the mechanism of control. While some of these techniques have already been implemented in real systems, other techniques involve serious complications and tough trade-offs. The present paper is intended to serve as the first comprehensive survey on the field of forebody shock control devices. The objectives of the present paper are multifold. The paper categorizes the various forebody shock control devices in a physics-based manner, explains the underlying physics for each device, and surveys the key studies and state-of-the-art knowledge. The paper also addresses the existing gaps in knowledge, highlights the existing systems implementing these devices, and discusses the associated practical implementation issues and design-tradeoffs. 2. Structural devices, the mechanical spikes: 2.1. Principle of operation of mechanical spikes Drag and Aeroheating Reduction Devices Fluidic Devices Opposing jets Structural Devices Mechanical spikes Energetic Devices Energy deposition Basic devices Structural-Fluidic Devices Structural-Energetic Devices Hybrid devices

show abstract

Section: Factors Controlling the Counterflow Effectivenessmentioning

confidence: 98%

Section: Derivatives Of Opposing Jet Device 371 Opposing Plasma Jetsmentioning

confidence: 99%

Section: Derivatives Of Opposing Jet Device 371 Opposing Plasma Jetsmentioning

confidence: 99%

See 1 more Smart Citation

Forebody shock control devices for drag and aero-heating reduction: A comprehensive survey with a practical perspective

Ahmed

Qin

2020

Progress in Aerospace Sciences

View full text Add to dashboard Cite

show abstract

“…Plasma actuators have been promising in controlling boundary layer flow separation. They have been used to reduce drag in a cone cylinder (Gainev et al 7 ) and in leading edge flow separation in high subsonic flow (Kelley et al 8 ). Samimy 9 also demonstrated the use of localized arc filament plasma actuators (LAFPAs) in high subsonic and supersonic flow for mixing enhancement, noise mitigation and flow field diagnostics.…”

Section: Introductionmentioning

confidence: 99%

Development and Characterization of Ultra-High Frequency Resonance-Enhanced Microjet Actuator

Upadhyay¹,

Gustavsson²,

Alvi³

2013

43rd Fluid Dynamics Conference

View full text Add to dashboard Cite

For flow control applications requiring very high frequency excitation, mechanical actuators often lack the durability or the control authority to be consistently useful in highspeed flows. High frequency excitation attempted in the past has been limited to either low frequency actuation with reasonable control authority or high frequency actuation with limited control authority due to limitation in frequency and amplitude of the actuators involved. In the present paper, an extension of previous development of the Resonance Enhanced Microjet actuators has been undertaken to extend the range of frequencies accessible beyond the range previously studied. Using lumped element model as well as empirical relationships developed in previous studies, two actuators have been designed with nominal frequencies of 25 kHz and 60 kHz. Extensive bench top characterization using acoustic measurements as well as optical diagnostics using a micro-schlieren setup was employed to characterize the frequency as well as amplitude of the actuator. The actuators performed at a range of frequencies 20.3-27.8 kHz and 54.8-78.2 kHz, respectively, as a function of NPR and impingement height. In addition to providing information on the actuator flow physics and the performance of the actuators with variations in operating conditions, the tests serve to develop an easy-to-integrate ultra-high frequency actuator for flow control in supersonic free shear and resonant flows. NomenclatureA. Latin d = source jet diameter [m] f = frequency [m] L = cavity depth [m] h = distance between source jet nozzle and cavity opening [m] h/d = normalized distance from the source jet NPR = source jet nozzle pressure ratio, P 0 /P amb [1] SPL = Sound Pressure level, relative to 20 µPa [dB] OASPL = Overall sound pressure level, integrated over spectrum, relative to 20 µPa [dB] P = static pressure [Pa] P 0 = source jet stagnation pressure [Pa] V = jet axial velocity [m/s] a = ambient speed of sound [m/s] M = Mach number, V/a B. Subscripts c = Cavity conditions m = Microjet conditions

show abstract

“…Heat transfer experimental data 19 received by the method of two-layer thermal-indicator coating 22 confirm this conclusion. Other applications of the gas blowing include the divert and attitude reaction control systems (see the review of Gimelshein et al 23 and original papers [24][25][26][27][28][29] ) and a counterflow drag reduction technique in high-speed systems (see the study of Josyula et al 30 and others [31][32][33] ).…”

Section: Introductionmentioning

confidence: 99%

Heat Transfer on a Hypersonic Sphere with Diffuse Rarefied-Gas Injection

Riabov

2004

42nd AIAA Aerospace Sciences Meeting and Exhibit

View full text Add to dashboard Cite

The interaction of a diffusing outgas flow from a sphere nose opposing a hypersonic free stream is studied numerically by the direct simulation Monte-Carlo technique under the transitional rarefied-gas-flow regime conditions at Knudsen numbers from 0.016 to 1.5 and blowing factors from 0.15 to 1.5. Strong influences of the blowing factor (the ratio of outgas mass flux to upstream mass flux) and the Knudsen number on the flow structure about a sphere (temperature fields, the configuration of mixing flow zones) and on heat distributions along the spherical surface have been found. At large blowing factors, the injected gas significantly reduces heat flux in wide area near the spherical nose. This effect is more pronounced for light gas (helium) injection in the near-continuum flow. Nomenclature d = orifice diameter, 0.002 m f = mole fraction of helium G w = mass injection rate ratio ("blowing" factor) Kn ∞,R = Knudsen number M = Mach number p = pressure, N/m 2 R = sphere radius, 0.015 m Re 0,R = Reynolds number St = Stanton number s = coordinate along a spherical surface T = temperature t w = temperature factor, T w /T 0 x = coordinate along an axis of body symmetry subscripts R = sphere radius as a length-scale parameter w = wall condition 0 = stagnation flow condition ∞ = freestream parameter

show abstract

Theoretical and experimental study of the possibility of reducing aerodynamic drag by employing plasma injection

Cited by 20 publications

References 0 publications

Forebody shock control devices for drag and aero-heating reduction: A comprehensive survey with a practical perspective

Forebody shock control devices for drag and aero-heating reduction: A comprehensive survey with a practical perspective

Development and Characterization of Ultra-High Frequency Resonance-Enhanced Microjet Actuator

Heat Transfer on a Hypersonic Sphere with Diffuse Rarefied-Gas Injection

Contact Info

Product

Resources

About