Plasma/wind tunnel experiment with 1/6 scale model of nose part of F-15

Beaulieu, W.; Bityurin, V. A.; Klimov, A. I.; Leonov, Sergey B.; Pashina, A.; Timofeev, B. T.

doi:10.2514/6.1999-4825

Cited by 3 publications

(5 citation statements)

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“…As an example the generation of re-circulating zones near the model can be mentioned. Fig.3 represents such data, which labeled as "pulse discharge on a needle" [38]. The problem of effectiveness decrease along with the improving of a model shape could be formulated in terms of effective form factor: blowing out of jet or creation of thermal in-hornogeneity in front of a blunted model leads to the change of streamlined effective shape.…”

Section: Problem Of Effective Form Factormentioning

confidence: 99%

“…The generation of non-equilibrium high energetic structural plasma formations -non-equilibrium plasmoids(NP) -in a gas and a gas flow was studied in [38,49,50]. In the course of these investigations high effective plasma generators of different types of NP were designed and used: HF streamer plasmoid, NP created by pulse repetitive discharge, NP created by AC discharge and combined discharge.…”

Section: Mhdandplasma Assisted Combustionmentioning

confidence: 99%

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EM advanced flow/flight control

Батенин

2001

39th Aerospace Sciences Meeting and Exhibit

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The status of research in a newly formulated area -Magneto-Plasma-Aerodynamics (MPA) for aerospace applications performed at Institute of High Temperatures of Russian Academy of Sciences is reviewed. Motivations, background, current tasks and future work plans are discussed. Promising areas for applications: total drag reduction, shock wave attenuation, plasma and MHD assisted high speed combustion, MHD flow control and on-board electrical power generation -are indicated. IntroductionDuring last decade a new approach to a control of air flow around vehicles is discussed with increasing intensity [1][2][3][4][5]. This approach is based on the controllable momentum and energy redistribution in up-coming flow by means of on-board generated external electrical and magnetic fields. The advantage of such an approach is related to the potentiality of the electromagnetic fields being able, in principle, to create a remote impact on flow parameters instead of the contact interaction of vehicle surface with airflow typically used in conventional gasdynamics. Properly distributed energy sources and sinks Q e = jE and the MHD body force F=jxB result in flow field modification and, in particular, gasdynamics parameters distribution over the vehicle surface. Pressure and skin friction on the vehicle surface define the total drag (or trust) and the total moment, whereas the temperature (enthalpy) defines the heat fluxes to the surface. Moreover, the plasma conditions in combination with external electric and magnetic fields can result in more or less significant modification of transport properties of the flowing media, such as viscosity, heat and electrical conductivity, and in change in the effective speed of sound, which is of primary importance especially for supersonic flow evolution over bodies. The heat release in up-coming flow as an effective technique to reduce the total drag and the peak heat flux of blunted bodies in supersonic flows are discussed in a number of papers [6][7][8]. It was shown that the properly localized concentrated heat release could provide a very significant total drag reduction with the rather high effectiveness when the energy consumption is much less than the drag force work decreasing. Such an energy deposition can be realized with one of the type of gas discharge already tested in laboratories: plasma jet (PJ) [9-10], the high frequency (HF) discharge of the capacitive type [11][12], the microwave discharge (MW) [13][14], the combined laser or e-beam + HF or MW discharge [15][16]. The pioneering studies of plasma aerodynamics effects were performed in 80 th in the former Soviet Union with shock tunnels [17-18] on the shock wave propagation

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Section: Problem Of Effective Form Factormentioning

confidence: 99%

Section: Mhdandplasma Assisted Combustionmentioning

confidence: 99%

EM advanced flow/flight control

Батенин

2001

39th Aerospace Sciences Meeting and Exhibit

Self Cite

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“…(7)-(10) yield (11) The set of equations (11) reduces to a single equation, Solutions of (11), which decay at y ∞, have the form…”

Section: Basic Equations and Range Of Investigationmentioning

confidence: 99%

“…An increase in disturbance gain is observed. Note further that the observed degree of initial turbulence in nonequilibrium gas flows appreciably exceeds that observed in equilibrium flows [11,12]. Both these factors necessitate the investigation of stability of two-dimensional boundary layer of nonequilibrium gas in the region of nonlinear critical layer, in the zone of space instability wave, and in the RSI.…”

Section: Introductionmentioning

confidence: 96%

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A nonlinear critical layer in nonequilibrium gas

2008

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The method of matched asymptotic expansions is used to analyze the evolution of disturbances of a nonequilibrium compressible boundary layer on a flat plate in the region of nonlinear critical layer. A dispersion relation is obtained for low-amplitude subsonic disturbances. An equation is derived, which describes the evolution of disturbance in the nonlinear stage of its development. It is demonstrated that, similar to the case of equilibrium media, the increase in the disturbance amplitude in the given stage of development of turbulence exhibits an explosive pattern. The characteristic time of instability decreases with increasing degree of disequilibrium of the medium.

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The Dynamics of Shock Dispersion and Interactions in Supersonic Freestreams with Counterflowing Jets

Daso

Pritchett

Wang

et al. 2007

45th AIAA Aerospace Sciences Meeting and Exhibit

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An active flow control concept using counterflowing jets to significantly modify the external flowfields and strongly weaken or disperse the shock-waves of supersonic and hypersonic vehicles to reduce the aerothermal loads and wave drag was investigated. Experiments were conducted in a trisonic blow-down wind-tunnel, complemented by pre-test computational fluid dynamics (CFD) analysis of a 2.6% scale model of Apollo capsule, with and without counterflowing jets, in Mach 3.48 and 4.0 freestreams, to assess the potential aerothermal and aerodynamic benefits of this concept. The model was instrumented with heat flux gauges, thermocouples and pressure taps, and employed five counterflowing jet nozzles (three sonic and other two supersonic with design Mach numbers of 2.44 and 2.94) and nozzle exit diameters ranging from 0.25 to 0.5 inch. Schlieren data show that at low jet flow rates of 0.05 and 0.1 lb,/sec, the interactions result in a long penetration mode (LPM) jet, while the short penetration mode (SPM) jet is observed at flow rates greater than 0. Ilb,/sec., consistent with the pre-test CFD predictions. For the LPM, the jet appears to be nearly hlly-expanded, resulting in a very unsteady and oscillatory flow structure in which the bow shock becomes highly dispersed such that it is no longer discernable. Higher speed camera Schlieren data reveal the shock to be dispersed into striations of compression waves, which suddenly coalesce to a weaker bow shock with a larger standoff distance as the flow rate reached a critical value. The pronounced shock dispersion could significantly impact the aerodynamic performance (L/D) and heat flux reduction of spacecrafk in atmospheric entry and re-entry, and could also attenuate the entropy layer in hypersonic blunt body flows. For heat transfer, the results show significant reduction in heat flux, even giving negative heat flux for some of the SPM interactions, indicating that the flow wetting the model is cooling, instead of heating the model, which could significantly impact the requirements and design of thermal protection system. These findings strongly suggest that the application of counterflowing jets as active flow control could have strong impact on supersonic and hypersonic vehicle design and performance. IntroductionOne of the technical challenges in space exploration and interplanetary missions is controlled entry and re-entry into planetary and Earth atmospheres, which requires the dissipation of considerable kinetic energy as the spacecrafk decelerates and penetrates the atmosphere. As such, effective heat load management of stagnation points and acreage heating remain a technological challenge and pose significant risk, especially for human missions.

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Plasma/wind tunnel experiment with 1/6 scale model of nose part of F-15

Cited by 3 publications

References 0 publications

EM advanced flow/flight control

EM advanced flow/flight control

A nonlinear critical layer in nonequilibrium gas

The Dynamics of Shock Dispersion and Interactions in Supersonic Freestreams with Counterflowing Jets

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