Preliminary experimental assessment of supersonic airflow behavior over ExoMars and X–43 inlet models using multiple flow regime shock tube

Kotov, M A; Ruleva, L. B.; Solodovnikov, S. I.; Суржиков, С. Т.

doi:10.1088/1742-6596/1009/1/012038

Cited by 4 publications

(1 citation statement)

References 12 publications

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“…In Kotov et al [13], the shock-wave structures appearing around the same hypersonic aircraft studied by the rest of the researchers cited in this paper were filmed using a high speed video camera and considering two different prototypes with small variations in the geometry. Visualisations of the flow at the engine entrance throat, where the shock waves reflected, were particularly interesting.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Study of the NASA’s X-43A Hypersonic Aircraft

Navó

Bergadà

2020

Applied Sciences

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A 2D aerodynamic study of the NASA’s X-43A hypersonic aircraft is developed using two different approaches. The first one is analytical and based on the resolution of the oblique shock wave and Prandtl–Meyer expansion wave theories supported by an in-house program and considering a simplified aircraft’s design. The second approach involves the use of a Computational Fluid Dynamics (CFD) package, OpenFOAM and the real shape of the aircraft. The aerodynamic characteristics defined as the lift and drag coefficients, the aerodynamic efficiency and the pitching moment coefficient are calculated for different angles of attack. Evaluations are made for an incident Mach number of 7 and an altitude of 30 km. For both methodologies, the required angles of attack to achieve a Vertical Force Balance (VFB) and a completely zero pitching moment conditions are considered. In addition, an analysis to optimise the nose configuration of the aircraft is performed. The mass flow rate throughout the scramjet as a function of the angle of attack is also presented in the CFD model in addition to the pressure, density, temperature and Mach fields. Before presenting the corresponding results, a comparison between the aerodynamic coefficients in terms of the angle of attack of both models is carried out in order to properly validate the CFD model. The paper clarifies the requirements needed to make sure that both oblique shock waves originating from the leading edge meet just at the scramjet inlet clarifying the advantages of fulfilling such condition.

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Section: Introductionmentioning

confidence: 99%

Aerodynamic Study of the NASA’s X-43A Hypersonic Aircraft

Navó

Bergadà

2020

Applied Sciences

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Review of experimental work performed at the hypersonic aerodynamic shock tube

Kotov¹,

Ruleva²,

Solodovnikov³

2018

AIP Conference Proceedings

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Experimental investigation of the thermal loads upon electrodynamic modification of supersonic flow around axisymmetrical body

Попов

Monakhov

Kotov

et al. 2020

IOP Conf. Ser.: Mater. Sci. Eng.

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The results of experimental studies of the magnetohydrodynamic (MHD) effect on the flow around an axisymmetric model of a supersonic nitrogen stream are presented. The magnetic field was created by a solenoid located on the cylindrical part of the model under the influence of a pulsed electric current flowing through the solenoid. A pulsed gas discharge was ignited on the conical surface of the model, acquiring rotation in the solenoidal magnetic field around the model axis. The effect of the magnetic field on the gas-dynamic structure of the flow near the model and the heat flux to its surface were investigated. In the experiments, schlieren pictures,fast photographic scans of the discharge glow were recorded, and heat flux was measured. The effect of a magnetic field on the gasdynamic structure of the flow near the model and the heat load to its surface were found. Also, the dependence of MHD effects on the polarity of external voltage source connecting was found.

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Preliminary experimental assessment of supersonic airflow behavior over ExoMars and X–43 inlet models using multiple flow regime shock tube

Cited by 4 publications

References 12 publications

Aerodynamic Study of the NASA’s X-43A Hypersonic Aircraft

Aerodynamic Study of the NASA’s X-43A Hypersonic Aircraft

Review of experimental work performed at the hypersonic aerodynamic shock tube

Experimental investigation of the thermal loads upon electrodynamic modification of supersonic flow around axisymmetrical body

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