Description and Flow Assessment of the Delft Hypersonic Ludwieg Tube

Schrijer, F.F.J.; Bannink, W.J.

doi:10.2514/6.2008-3943

Cited by 8 publications

(8 citation statements)

References 6 publications

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“…The experiments are performed in the Hypersonic Test Facility Delft [27]. The HTFD is a cold hypersonic wind tunnel that operates according to the Ludwieg tube concept that provides Mach 7.5 airflow in a 350 test section.…”

Section: Methodsmentioning

confidence: 99%

“…Therefore by introducing this delay only the temperature information is used for the period that the tunnel is properly started. As a matter of fact, Schrjier and Bannink [27] showed that stationary flow conditions start approximately 25 ms after the valve opening by measuring the pressure variation in the settling chamber. In figure 1 the comparison between the experimental temperature rise and the heat equation after the introduction of the delay is reported, as can be seen the first 30 ms are neglected.…”

Section: Measurement Techniquementioning

confidence: 99%

See 1 more Smart Citation

IR thermography investigation on roughness induced transition in high-speed flows

Avallone¹,

Schrijer²,

Cardone³

2014

Proceedings of the 2014 International Conference on Quantitative InfraRed Thermography

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Boundary layer transition in high-speed flows is a phenomenon that despite extensive research over the years is still extremely hard to predict. The presence of protrusions or gaps can lead to an accelerated laminar-to-turbulent transition enhancing the thermal loads and the skin friction coefficient. In the current investigation, high-resolution heat transfer measurements using infrared thermography are performed on the flow past several different roughness geometries (cylinders and pizza-box) at free stream Mach number equal to 7.5 and three unit Reynolds number (14 • 10 , 11 • 10 , 8 • 10 ). The roughness elements are applied on a plate that is oriented at a 5° angle of attack with respect to the flow direction. For each Reynolds number the roughness element is positioned at 30 mm and at 60 mm from the leading edge. The measurements establish the roughness effectiveness in promoting transition and they provide insight into the flow topology.

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Section: Methodsmentioning

confidence: 99%

Section: Measurement Techniquementioning

confidence: 99%

IR thermography investigation on roughness induced transition in high-speed flows

Avallone¹,

Schrijer²,

Cardone³

2014

Proceedings of the 2014 International Conference on Quantitative InfraRed Thermography

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“…Sounding rockets are a fast emerging technology giving low-cost access to space [ 1 ]. Sounding rockets also provide important data on aerodynamics at speeds up to hypersonic [ 2 ], which are typically very difficult to achieve in wind tunnels [ 3 , 4 ]. A University of Canterbury Rocketry Research Group [ 5 ] has been formed to develop control systems for high accuracy positioning with a longer term goal of stabilizing rockets through the sound barrier.…”

Section: Introductionmentioning

confidence: 99%

Minimal modelling approach to describe turbulent rocket roll dynamics in a vertical wind tunnel

Hann

Snowdon

Rao

et al. 2011

Proceedings of the Institution of Mechanical Engineers, Part G:

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The roll dynamics of a 5-kg, 1.3 -m high sounding rocket are analysed in a vertical wind tunnel. Significant turbulence in the tunnel makes the system identification of the effective inertia, damping, and asymmetry with respect to roll challenging. A novel method is developed, which decouples the disturbance from the rocket frame's intrinsic roll dynamics and allows accurate prediction of roll rate and angle. The parameter identification method is integral-based, and treats wind disturbances as equivalent to a movement in the actuator fins. The method is robust, requires minimal computation, and gave realistic disturbance distributions reflecting the randomness of the turbulent wind flow. Two models, one with constant damping and one with fin angle-dependant damping were considered. The mean absolute roll rate of the rocket frame observed in experiments was 16.4°/s and both models predicted the roll rate with a mean absolute error less than 0.10°/s with a standard deviation less than 0.08°/s. The roll angle (measured by an encoder), was tracked by the model with a mean absolute error less than 0.20° and a standard deviation less than 0.15°. These results prove the concept of this minimal modelling approach which will be extended to varying wind speed, and pitch, and yaw dynamics in the future.

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“…A nozzle insert creates a throat area in order to choke the flow, thus preventing flow disturbances from travelling upstream. For this reason, the throat is located upstream of the sealing, as opposite to solutions that are typical in Ludwieg tubes (Schrijer and Bannink 2010;Knauss et al 1999). It can be moved remotely in the longitudinal direction to change the throat area section between approximately 420 and 600 mm 2 , and this allows to modulate the strength of the rarefaction waves.…”

Section: Equipment and Proceduresmentioning

confidence: 99%

The flexible asymmetric shock tube (FAST): a Ludwieg tube facility for wave propagation measurements in high-temperature vapours of organic fluids

et al. 2015

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(2) the process start-up time of the valve has been found to be between 2.1 and 9.0 ms, (3) preliminary rarefaction wave experiments in the dense vapour of siloxane D 6 (dodecamethylcyclohexasiloxane, an organic fluid) were successfully accomplished up to temperatures of 300 • C, and (4) a method for the estimation of the speed of sound from wave propagation experiments is proposed. Results are found to be within 2.1 % of accurate model predictions for various gases. The method is then applied to estimate the speed of sound of D 6 in the NICFD regime. List of symbols cSpeed of sound The set-up is equipped with a special fast-opening valve, separating the high-pressure charge tube from the lowpressure plenum. When the valve is opened, a wave propagates into the charge tube. The wave speed is measured using a time-of-flight technique employing four pressure transducers placed at known distances from each other. The first tests led to the following results: (1) the leakage rate of 5 × 10 −4 mbar l s −1 for subatmospheric and 5 × 10 −2 mbar l s −1 for a superatmospheric pressure is compatible with the purpose of the conceived experiments,

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Description and Flow Assessment of the Delft Hypersonic Ludwieg Tube

Cited by 8 publications

References 6 publications

IR thermography investigation on roughness induced transition in high-speed flows

IR thermography investigation on roughness induced transition in high-speed flows

Minimal modelling approach to describe turbulent rocket roll dynamics in a vertical wind tunnel

The flexible asymmetric shock tube (FAST): a Ludwieg tube facility for wave propagation measurements in high-temperature vapours of organic fluids

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