Effects of steady flow heating by arc discharge upstream of non-slender bodies

Schülein, Erich; Zheltovodov, A. A.

doi:10.1007/s00193-011-0307-1

Cited by 41 publications

(20 citation statements)

References 45 publications

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“…Despite some impressive findings, large quantitative discrepancies in the efficiency indicated in different studies are not always easy to explain. 8 To the author's knowledge, a reliable engineering method for the fast determination of the flow-heating effect on the wave-drag reduction does not exist at the moment. The aim of the present work was to develop and to validate such a method suitable for parameter studies.…”

Section: Introductionmentioning

confidence: 97%

Simplified model for flow-heating effect on wave drag of blunt bodies and its validation

Schülein

2015

45th AIAA Fluid Dynamics Conference

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Simplified analytical method for determination of flow-heating effects on the wave drag of bodies based on the modeling of the thermal-spike phenomenon is presented. Some existing model conceptions addressing certain aspects of this phenomenon were complemented and refined to develop a method suitable for parameter studies. This method was adjusted using available results for the Mach 3 supersonic flow over conically nosed bodies, and then validated by experimental and numerical results for different blunt bodies with hemispherical, flat and conical front faces. The ability to predict analytically the influence of some crucial parameters has successfully been demonstrated for the heat input ratio at steady and periodic heating, the normalized heated-wake/filament diameter, the Mach number and the specific heat capacity.

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Section: Introductionmentioning

confidence: 97%

Simplified model for flow-heating effect on wave drag of blunt bodies and its validation

Schülein

2015

45th AIAA Fluid Dynamics Conference

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“…The reduction of drag force together with the decrease of the stagnation parameters was obtained experimentally and numerically for air, in particular, in [9][10][11]. Effects of a local heating on wave drag reduction were investigated in [12][13][14]. Additionally, it has been stated that the triple-shock configurations accompanied by the vortex-contact structures were generated at the beginning stage of the process of energy release-shock layer interaction when the flow mode is close to the self-similar one [15][16][17].…”

Section: Introductionmentioning

confidence: 99%

Control of Triple-Shock Configurations and Vortex Structures Forming in High Speed Flows of Gaseous Media past an AD Body under the Action of External Energy Sources

Azarova

Gvozdeva

2017

Aerospace

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Abstract:The problem of supersonic streamlining of an aerodynamic (AD) body, "a plate blunted by a cylinder", by a flow with the freestream Mach number M = 4 containing an external energy source has been studied, taking into account physicochemical transformations. The results of the effect of the ratio of specific heats γ changing in the range from 1.1 to 1.4 on the dynamics of triple-shock configurations and vortex-contact structures are presented for the interaction of an energy source with the bow shock wave. The energy source is modeled via the heated rarefied layer (filament). The angles in the triple-shock configurations, the stagnation pressure, together with the frontal drag force, have been studied dependent on the specific heats ratio γ, the characteristics of the energy source, and also on the angle of the incident shock. Vortex-contact structures have been researched for the Mach numbers 7, 8, 9, as well as the generation of the Richtmyer-Meshkov instability accompanying the formation of a triple-shock configuration. The results show a strong influence of the specific heats ratio of the gas medium and the parameters of the energy source on the triple-shock configuration and aerodynamic characteristics of the body. This conclusion can be useful for aerospace applications in the area of the design of nozzles, intakes, and high speed flying vehicles. Additionally, the results show the possibility of flow control in the atmospheres of other planets using external energy deposition.

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“…Most of them base on the same physical principle that in the case of an aerospike leads to a reduction of the wave drag. The concepts range from heating the air in front of the blunt body by laser pulses (see, e. g., [7 9]), direct-current arc discharge (see, e. g., [10]), or with a electrically heated wire pointing upstream [11]. Also, the upstream injection of a jet originating from the nose tip showed promising results.…”

Section: Introductionmentioning

confidence: 99%

Wave drag reduction with a self-aligning aerodisk on a missile configuration

Schnepf

Wysocki

Schülein

2017

Progress in Flight Physics

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A self-aligning aerodisk to reduce the wave drag on a pitching missile is numerically investigated. The motion and the Mach number were chosen to match a maneuver §ight of an actual missile: pitching frequency f = 7.5 Hz, Mach number M = 2.2, and range of angle of attack 0 • < α < 21 • . The self-alignment was realized with a coupling of the §ow solver with a 6DoF (6 degrees of freedom) tool. In the entire range of angle of attack, the drag could be reduced with the self-aligning aerodisk. A comparison with experimental data showed in parts a quite good agreement in the aerodynamic coe©cients, in the shock structure, and in the alignment of the aerodisk.

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Effects of steady flow heating by arc discharge upstream of non-slender bodies

Cited by 41 publications

References 45 publications

Simplified model for flow-heating effect on wave drag of blunt bodies and its validation

Simplified model for flow-heating effect on wave drag of blunt bodies and its validation

Control of Triple-Shock Configurations and Vortex Structures Forming in High Speed Flows of Gaseous Media past an AD Body under the Action of External Energy Sources

Wave drag reduction with a self-aligning aerodisk on a missile configuration

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