A comparison of disturbance levels measured in hypersonic tunnels using a hot-wire anemometer and a pitot pressure probe

Stainback, P. C.; Wagner, R. D.

doi:10.2514/6.1972-1003

Cited by 23 publications

(23 citation statements)

References 4 publications

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“…16, the angled acoustic disturbances (θ 120 deg) produce a much better match to experimental data than flow-parallel fast acoustic disturbances (θ 0 deg) [34]. The results suggest that, with judiciously imposed freestream disturbances, the method of computing the transfer function using DNS of flow around pitot probes holds the potential to ultimately be used to replace the unsteady approach of Stainback and Wagner [33] for recovering freestream disturbance spectrum from stagnation pressure spectrum for hypersonic pitot probes. Experiments and DNS also suggest an unexpected dependence of transfer functions on sleeve geometries and Reynolds numbers.…”

Section: Recovery Of Tunnel Freestream Disturbancesmentioning

confidence: 85%

“…Researchers have previously attempted to account for the difference between a pitot-probe-measured spectrum and a freestream spectrum, including the so-called quasisteady analysis by Harvey et al [32] and the unsteady analysis by Stainback and Wagner [33]. The quasisteady analysis was found to significantly underpredict the pitot-probe fluctuations.…”

Section: Recovery Of Tunnel Freestream Disturbancesmentioning

confidence: 99%

See 1 more Smart Citation

Characterization of Freestream Disturbances in Conventional Hypersonic Wind Tunnels

Duan

Choudhari²,

Chou³

et al. 2019

Journal of Spacecraft and Rockets

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Although low-disturbance ("quiet") hypersonic wind tunnels are believed to provide more reliable extrapolation of boundary-layer transition behavior from ground to flight, the presently available quiet facilities are limited to Mach 6, moderate Reynolds numbers, low freestream enthalpy, and subscale models. As a result, only conventional ("noisy") wind tunnels can reproduce both Reynolds numbers and enthalpies of hypersonic flight configurations and must therefore be used for flight vehicle test and evaluation involving high Mach number, high enthalpy, and larger models. This paper outlines the recent progress and achievements in the characterization of tunnel noise that have resulted from the coordinated effort within the AVT-240 specialists group on hypersonic boundary-layer transition prediction. The new experimental measurements cover a range of conventional wind tunnels with different sizes and Mach numbers from 6 to 14 and extend the database of freestream fluctuations within the spectral range of boundary-layer instability waves over commonly tested models. New direct numerical simulation datasets elucidate the physics of noise generation inside the turbulent nozzle wall boundary layer, characterize the spatiotemporal structure of the freestream noise, and account for the propagation and transfer of the freestream disturbances to a Pitot-mounted sensor.

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Section: Recovery Of Tunnel Freestream Disturbancesmentioning

confidence: 85%

Section: Recovery Of Tunnel Freestream Disturbancesmentioning

confidence: 99%

Characterization of Freestream Disturbances in Conventional Hypersonic Wind Tunnels

Duan

Choudhari²,

Chou³

et al. 2019

Journal of Spacecraft and Rockets

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show abstract

“…A measurement of the normalized pitot pressure has been accepted as a standard method to characterize the freestream disturbance level in the test section [52]. As introduced by Beckwith and Moore [53], the freestream disturbance level in our experiment is evaluated by a Kulite XCQ-062-25 pressure transducer, which is flush-mounted in the tapered tip of a stainless steel rod and located at the center of the nozzle exit.…”

Section: A Test Facilitymentioning

confidence: 99%

Transition in Hypersonic Boundary Layers: Role of Dilatational Waves

et al. 2016

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Transition and turbulence production in a hypersonic boundary layer is investigated in the Mach 6 wind tunnel at Peking University, using Rayleigh-scattering visualization, fast-response pressure measurements, and particle image velocimetry. Detailed analysis of the experimental observations is provided. It is found that, although the second mode is primarily an acoustic wave, it causes the formation of high-frequency vortical waves. Moreover, the second mode interacts strongly with low-frequency waves, which leads to immediate transition to turbulence.freestream velocity, m∕s u = velocity vector, m∕s u = x component of the velocity, m∕s v = y component of the velocity, m∕s w = z component of the velocity, m∕s x = streamwise coordinate along the cone's surface, mm y = coordinate normal to the cone's surface, mm z = transverse coordinate normal to the x-y plane, mm= viscous normal stress, Pa ρ = density, kg∕m 3 τ f = flow time scale, s τ p = particle relaxation time, s Φ = viscous dissipation function per unit volume, kg∕m · s 3 ω = vorticity, 1∕s

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“…Disturbances in hypersonic wind tunnels are dominated by sound waves, which are radiated by the turbulent boundary layers of the nozzle walls (Kovasznay 1953;Laufer 1961). A measurement of the normalized Pitot pressure is the standard method of characterizing the free-stream disturbance level in the test section (Stainback 1972). As introduced by Beckwith & Moore (1982), the free-stream disturbance level in our experiments was evaluated using a Kulite XCQ-062-25 pressure transducer that was flush-mounted in the tapered tip of a stainless steel rod and located at the centre of the nozzle exit.…”

Section: Facilitymentioning

confidence: 99%

Dilatational-wave-induced aerodynamic cooling in transitional hypersonic boundary layers

Zhu

et al. 2021

J. Fluid Mech.

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A comparison of disturbance levels measured in hypersonic tunnels using a hot-wire anemometer and a pitot pressure probe

Cited by 23 publications

References 4 publications

Characterization of Freestream Disturbances in Conventional Hypersonic Wind Tunnels

Characterization of Freestream Disturbances in Conventional Hypersonic Wind Tunnels

Transition in Hypersonic Boundary Layers: Role of Dilatational Waves

Dilatational-wave-induced aerodynamic cooling in transitional hypersonic boundary layers

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