High-Speed Schlieren Analysis of Retropropulsion Jet in Mach 10 Flow

Bathel, Brett F.; Litzner, Chase R.; Jones, Stephen B.; Berry, Scott A.; Smith, Norman F.; Garbeff, Theodore J.

doi:10.2514/1.a34522

Cited by 10 publications

(2 citation statements)

References 32 publications

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“…The differences between experimental and numerical pressure values may be caused by numerical limitations in correctly capturing the redirection of the jet flow. Furthermore, unsteady effects were observed in the flowfield similar to those observed by Bathel et al [13], which may also lead to discrepancies between experiments and the steady-state RANS computations.…”

Section: Cfd Validationsupporting

confidence: 67%

“…A Photron Fastcam SA-X2 captured these images at a frequency of 12,500 Hz, an exposure time of 2.5 μs, and with a resolution of 1024 × 1024 pixel. The locations of bow shock, contact surface, terminal shock, and triple point were manually extracted from the coefficient of variant images similar to a study on high-speed schlieren of SRP flows by Bathel et al [13]. These images were produced from the captured high-speed schlieren images of each run.…”

Section: A Experimental Methodsmentioning

confidence: 99%

See 1 more Smart Citation

Similarity and Key Parameters of Retropropulsion Assisted Deceleration in Hypersonic Wind Tunnels

Gutsche

Ansgar

Gülhan

2021

Journal of Spacecraft and Rockets

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Section: Cfd Validationsupporting

confidence: 67%

Section: A Experimental Methodsmentioning

confidence: 99%

Similarity and Key Parameters of Retropropulsion Assisted Deceleration in Hypersonic Wind Tunnels

Gutsche

Ansgar

Gülhan

2021

Journal of Spacecraft and Rockets

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Aerodynamic characteristics of the retro propulsion landing burn of vertically landing launchers

Marwege,

Gülhan

2024

Exp Fluids

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In the frame of the European funded H2020 project RETALT (retro propulsion-assisted landing technologies), the unsteady aerodynamics of vertically descending and landing launchers have been investigated. In this paper, experimental data of the landing burn tested in the Vertical Free-Jet Facility Cologne at DLR in Cologne are presented. The landing burn was simulated with a cold gas jet of pressurized air opposing the wind tunnel free stream. Tests with several jet conditions were compared to results without active jet. Proper orthogonal decomposition of schlieren recordings and spectral analyses of their time histories are performed and are compared to frequencies in pressure measurements. Dominant frequencies were found, which are strongest at Mach 0.8. Especially, a Strouhal number of 0.2 was found to be most dominant. The intensity of the dominant frequencies can be lowered if the engine is active. The normalized root mean square pressure fluctuations are between 0.1 and 0.3 during the landing maneuver. Additionally, the steady flow features scale well with the ambient pressure ratio and the momentum flux ratio. The unsteady flow field dynamics of the subsonic retro propulsion flow field can likely be linked to large-scale turbulent structures in the supersonic jet, triggering large-scale pressure fluctuations and altering the overall flow field.

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High-Speed Self-Aligned Focusing Schlieren and Background-Oriented Schlieren with Pulsed Laser Illumination

Bathel,

Weisberger,

Boyda

et al. 2024

Optica Sensing Congress 2024 (AIS, LACSEA, Sensors, QSM)

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Laser light sources are commonly used in schlieren-based flow visualization techniques that are in development at NASA Langley Research Center. Of particular interest are high-intensity, low coherence sources that allow for high signal-to-noise schlieren imagery to be acquired without the laser speckle that typically occurs as a result of interference. Results from a self-aligned focusing schlieren system developed at NASA Langley and a background-oriented schlieren system are presented to highlight the effectiveness of these sources.

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High-Speed Schlieren Analysis of Retropropulsion Jet in Mach 10 Flow

Cited by 10 publications

References 32 publications

Similarity and Key Parameters of Retropropulsion Assisted Deceleration in Hypersonic Wind Tunnels

Similarity and Key Parameters of Retropropulsion Assisted Deceleration in Hypersonic Wind Tunnels

Aerodynamic characteristics of the retro propulsion landing burn of vertically landing launchers

High-Speed Self-Aligned Focusing Schlieren and Background-Oriented Schlieren with Pulsed Laser Illumination

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