Performance data of the new free-piston shock tunnel T5 at GALCIT

Hornung, H. G.; Sturtevant, B.; Bélanger, Jacques; Sanderson, S. R.; Brouillette, Martin; Jenkins, Marion K.

doi:10.1007/978-3-642-77648-9_95

Cited by 33 publications

(13 citation statements)

References 3 publications

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“…Flows at this high specific kinetic energy can only be produced in the laboratory for durations on the order of 2 ms before the surface temperature of the wind tunnel nozzle throat exceeds working limits. The rationale and operation of free piston shock tunnels are described by Stalker 6 and Hornung et al 7 for the interested reader.…”

Section: Resultsmentioning

confidence: 99%

Transient heat flux measurement using a surface junction thermocouple

Sanderson¹,

Sturtevant²

2002

Review of Scientific Instruments

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A new form of surface junction thermocouple sensor has been developed and tested. The novel feature of the design is the use of a tapered fit between two coaxial thermocouple elements to form a thin, robust junction. The gauge has a response time on the order of 1 s and is suitable for measuring large transient heat fluxes in hypervelocity wind tunnels. Asymptotic analysis is used to demonstrate the operating principles and to assess the errors associated with the finite thickness of the surface junction. Spectral deconvolution methods are used to infer a mean square optimal estimate of the surface heat flux from time resolved surface temperature measurements. This improved signal processing method is applicable to transient heat flux gauges of all types. Potential reducible error sources and other systematic errors are described. Measurements of the heat flux about the forebody of a cylindrical body in a hypervelocity flow demonstrate the functioning of the gauge and are used to obtain statistical estimates of the repeatability of the technique. The measured heat fluxes are compared with established theoretical predictions.

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Section: Resultsmentioning

confidence: 99%

Transient heat flux measurement using a surface junction thermocouple

Sanderson¹,

Sturtevant²

2002

Review of Scientific Instruments

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“…This facility is described in detail in Hornung et al [7] Briefly, T5 is a piston-driven reflected shock tunnel that generates hypervelocity flows which simulate real gas flight environments. A piston driven by high pressure air is used to heat and accelerate a driver gas to a high temperature and pressure in a very short time.…”

Section: Methodsmentioning

confidence: 99%

Modeling of Shock Tunnel Aeroheating Data on the Mars Science Laboratory Aeroshell

Wright

Olejniczak

Brown

et al. 2006

Journal of Thermophysics and Heat Transfer

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A series of shots are run in the T5 shock tunnel at California Institute of Technology to measure heating levels on a 70 blunt cone at angle of attack in an environment representative of the Mars Science Laboratory entry. Twenty shots are obtained in CO 2 over a range of enthalpies and pressures chosen to span the laminar and turbulent flow regimes. The data indicate that the lee side turbulent heating augmentation predicted by flight simulations is valid and must be accounted for during the design of the thermal protection system. Computational fluid dynamic simulations are generally in good agreement with the laminar data when employing a supercatalytic wall model, whereas turbulent simulations are in reasonable agreement when a noncatalytic wall model is used. The reasons for this discrepancy are unknown at this time. The turbulent heating augmentation is shown to be inversely related to freestream enthalpy. Changes in angle of attack between 11 and 16 are shown to have minimal impact on measured and computed heating. A transition criterion based on momentum thickness Reynolds number, analogous to that used in flight predictions, predicts onset with reasonable accuracy, although transition is observed to occur later than the current design criterion indicates.

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“…T5 is capable of producing stagnation pressures of up to 80 MPa, and flow speeds are typically in the range 3-6 km/s, sufficient to reproduce many of the real-gas effects that are present in real hypervelocity flows. Further information regarding the T5 facility may be found in Hornung et al (1991).…”

Section: The T5 Hypervelocity Shock Tunnel Facilitymentioning

confidence: 99%

Proximal bodies in hypersonic flow

2007

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The problem of proximal bodies in hypersonic flow is encountered in several important situations, both natural and man-made. The present work seeks to investigate one aspect of this problem by exploring the forces experienced by a secondary body when some part of it is within the shocked region created by a primary body travelling at hypersonic speeds.An analytical methodology based on the blast wave analogy is developed and used to predict the secondary force coefficients for simple geometries in both two and three dimensions. When the secondary body is entirely inside the primary shocked region, the nature of the lateral coefficient is found to depend strongly on the relative size of the two bodies. For two spheres, the methodology predicts that the secondary body will experience an exclusively attractive lateral force if the secondary diameter is larger then one-sixth the primary diameter. The analytical results are compared with numerical simulations carried out using the AMROC software and good agreement is obtained if an appropriate normalization for the lateral displacement is used.Results from a series of experiments in the T5 hypervelocity shock tunnel are also presented and compared with perfect-gas numerical simulations, again with good agreement. In order to model this situation experimentally, a new force-measurement technique for short-duration hypersonic facilities has been developed, and results from the validation experiments are included.Finally, the analytical methodology is used to model two physical situations. First, the entry of a binary asteroid system into the Earth's atmosphere is simulated. Seciv ond, a model for a fragmenting meteoroid in a planetary atmosphere is developed, and simulations are carried out to determine whether the secondary scatter patterns in the Sikhote-Alin crater field may be attributed to aerodynamic interactions between fragments rather than to secondary fragmentation. It is found that while aerodynamic interactions lead to increased secondary crater grouping, these groups do not exhibit the typically elliptical shape that we would expect secondary fragmentation to produce.

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Performance data of the new free-piston shock tunnel T5 at GALCIT

Cited by 33 publications

References 3 publications

Transient heat flux measurement using a surface junction thermocouple

Transient heat flux measurement using a surface junction thermocouple

Modeling of Shock Tunnel Aeroheating Data on the Mars Science Laboratory Aeroshell

Proximal bodies in hypersonic flow

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