Separation process of multi-spheres in hypersonic flow

Park, Seong-Hyeon; Park, Gisu

doi:10.1016/j.asr.2019.10.009

Cited by 25 publications

(9 citation statements)

References 22 publications

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“…Laurence, Parziale & Deiterding (2012) conducted both experiments and simulations of separating spheres at Mach 4, and found that . Further investigations of this or similar problems have been carried out, for example, by Park & Park (2020) and Register et al. (2020).…”

Section: Introductionmentioning

confidence: 98%

“…Laurence, Parziale & Deiterding (2012) conducted both experiments and simulations of separating spheres at Mach 4, and found that V T = 0.24. Further investigations of this or similar problems have been carried out, for example, by Park & Park (2020) and Register et al (2020). In such configurations, the mutual repulsion of the two bodies is caused by the confined, high-pressure region that develops between them when they are closely spaced.…”

Section: Introductionmentioning

confidence: 99%

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Dynamics of a spherical body shedding from a hypersonic ramp. Part 1. Inviscid flow

2020

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Section: Introductionmentioning

confidence: 98%

Section: Introductionmentioning

confidence: 99%

Dynamics of a spherical body shedding from a hypersonic ramp. Part 1. Inviscid flow

2020

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“…In the acceleration measurement-based techniques, the model support is removed or weakened in order to obtain the acceleration of the test model. For the FFT, detachable supports, which allow the test model to move freely during the test time, are adopted to measure the acceleration of the lightweight test model [6,10,11]. By using the detachable supports, the aerodynamic forces can be measured, minimizing flow disturbance from the model supports.…”

Section: Introductionmentioning

confidence: 99%

Assessment of drag measurement techniques in a shock tunnel

et al. 2022

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Three force measurement techniques in a shock tunnel, the free-flight, movable-support force balance, and stress-wave force balance techniques were employed, and each technique’s characteristics were assessed. For each force measurement technique, the system setup, data processing method, measurement uncertainties, and applied range of the test model size-flow establishment time were described in detail and compared. For a comparison and discussion, the drag coefficients of a circular pointed cone model with a semi-angle of 18.4° at a nominal freestream Mach number of 6 were measured. As a result, three force measurement techniques yield similar drag coefficients. However, the measurement uncertainties were increased in the order of the free-flight, the stress-wave force balance, and the movable-support force balance techniques. The main causes of the measurement uncertainties were the corner detection uncertainties for the free-flight techniques, and the propagation of the internal or external vibrations for the movable-support and stress-wave force balance techniques. To estimate the appropriate range of the test model size and flow establishment time for each technique’s application, the force measurement systems of the present work and the available literature were compared. As a result of comparative discussion, force measurement environments that can be advantageous for each technique are suggested.

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“…Aerodynamics of simple-shaped bodies in high-speed flows is generating renewed interest in the field of atmospheric entry of meteoroids, space debris and separating components of launch systems. Especially in the past decade, the characterization of flowfields around single (Lee et al 2017;Seltner et al 2019;Rees et al 2020;Grossir et al 2020) and multiple bodies (Laurence et al 2012;Marwege et al 2018;Park and Park 2020;Register et al 2020) has gained importance with respect to fragmentation, demise and separation behaviors of these space objects undergoing atmospheric entry. The determination of their flight trajectories helps to predict the impact area of uncontrolled entering spacecrafts with the objective to protect persons and properties from harm.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamics of inclined cylindrical bodies free-flying in a hypersonic flowfield

et al. 2021

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The influence of the flight attitude on aerodynamic coefficients and static stability of cylindrical bodies in hypersonic flows is of interest in understanding the re/entry of space debris, meteoroid fragments, launch-vehicle stages and other rotating objects. Experiments were therefore carried out in the hypersonic wind tunnel H2K at the German Aerospace Center (DLR) in Cologne. A free-flight technique was employed in H2K, which enables a continuous rotation of the cylinder without any sting interferences in a broad angular range from 0$$^{\circ }$$ ∘ to 90$$^{\circ }$$ ∘ . A high-speed stereo-tracking technique measured the model motion during free-flight and high-speed schlieren provided documentation of the flow topology. Aerodynamic coefficients were determined in careful post-processing, based on the measured 6-degrees-of-freedom (6DoF) motion data. Numerical simulations by NASA’s flow solvers Cart3D and US3D were performed for comparison purposes. As a result, the experimental and numerical data show a good agreement. The inclination of the cylinder strongly effects both the flowfield and aerodynamic loads. Experiments and simulations with concave cylinders showed marked difference in aerodynamic behavior due to the presence of a shock–shock interaction (SSI) near the middle of the model. Graphic abstract

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Separation process of multi-spheres in hypersonic flow

Cited by 25 publications

References 22 publications

Dynamics of a spherical body shedding from a hypersonic ramp. Part 1. Inviscid flow

Dynamics of a spherical body shedding from a hypersonic ramp. Part 1. Inviscid flow

Assessment of drag measurement techniques in a shock tunnel

Aerodynamics of inclined cylindrical bodies free-flying in a hypersonic flowfield

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