Initial Results From a Low Density, Hypervelocity Wind Tunnel

Potter, Jan; Kinslow, Max; Arney, George D.; Bailey, A. B.

doi:10.1016/b978-0-12-395595-1.50029-5

Cited by 16 publications

(4 citation statements)

References 5 publications

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“…The blunter shapes have larger diffuse shock structures that are more susceptible to interference with a growing windtunnel boundary layer. Unfortunately, available references [20][21][22] do not provide sufficient details of the windtunnel geometry in order to adequately simulate the windtunnel test to accurately capture the growing wall boundary layer from the nozzle and determine the boundary layer effects on the windtunnel model aerodynamics. From this study, it is recommended that more rarefied hypersonic windtunnel tests be conducted to broaden the existing literature, and that corresponding documentation be sufficiently detailed to enable comprehensive numerical simulation of the windtunnel tests.…”

Section: Discussionmentioning

confidence: 99%

“…Thus, the windtunnel data for the blunter shapes may be inaccurate because of disregarded wall effects. Unfortunately, available references [20][21][22] do not provide sufficient details of the windtunnel geometry in order to adequately simulate the windtunnel test to accurately capture the growing wall boundary layer from the nozzle and determine the boundary layer effects on the windtunnel model aerodynamics.…”

Section: B Blunted-cone Simulationsmentioning

confidence: 99%

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Assessment of Rarefied Hypersonic Aerodynamics Modeling and Windtunnel Data

Padilla

Boyd

2006

9th AIAA/ASME Joint Thermophysics and Heat Transfer Conference

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Section: Discussionmentioning

confidence: 99%

Section: B Blunted-cone Simulationsmentioning

confidence: 99%

Assessment of Rarefied Hypersonic Aerodynamics Modeling and Windtunnel Data

Padilla

Boyd

2006

9th AIAA/ASME Joint Thermophysics and Heat Transfer Conference

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“…1) is a continuous-type, arc-heated, ejector-pumped design. The major components are (1) d-c arc-heater of the constricted, non-rotated arc and non-swirl gas injection type, with a 40-kw power supply, (2) settling section of variable size but normally of 3-in. diameter and 6.25-to 10-in.…”

Section: Description Of Present Experiments 21 Wind Tunnelmentioning

confidence: 99%

“…This information was combined as shown in Eq. (1) to determine a correction when oversize probes and severe axial gradients were involved.…”

Section: Influence Of Axial Freestream Flow Gradientmentioning

confidence: 99%

Pressures in the Stagnation Regions of Blunt Bodies in the Viscous-Layer to Merged-Layer Regimes of Rarefied Flow

Potter¹,

Bailey²

1963

Conference on Physics of Entry Into Planetary Atmospheres

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Experimental data on pressures in the stagnation regions of hemispherical and flat noses on axisymmetric bodies in rarefied, hypersonic flow are presented. Diatomic and monatomic gases were used in the study, thereby illustrating the effect of molecular structure on the impact pressure. The experiments were conducted with the models in both cold-wall and insulated-wall conditions. It is concluded that impact pressures may be smaller than the corresponding inviscid values, although this reduction may amount to only a few percent. Small influences of wall heat transfer and molecular structure on impact pressure at a given Reynolds number are demonstrated. Pressure distribution on highly cooled, flat and hemispherical noses are predicted with generally acceptable accuracy by theories for inviscid flows. Flow conditions for these experiments were such that the Knudsen number of a full-scale nose having a radius of one foot and moving with hypersonic speed at altitudes of roughly 300, 000 ft was duplicated.. Thus, this report concerns the viscous-layer to merged-layer regimes of flow at altitudes above Earth where thermochemical reactions in the shock layers of blunt bodies are believed to be essentially frozen. PUBLICATION REVIEW This report has been reviewed and publication is approved.

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A Low-Load Three-Component Force Balance for Measurements in a Low-Density Wind Tunnel

Arney¹,

Harter²

1965

IEEE Trans. Aerosp.

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Initial Results From a Low Density, Hypervelocity Wind Tunnel

Cited by 16 publications

References 5 publications

Assessment of Rarefied Hypersonic Aerodynamics Modeling and Windtunnel Data

Assessment of Rarefied Hypersonic Aerodynamics Modeling and Windtunnel Data

Pressures in the Stagnation Regions of Blunt Bodies in the Viscous-Layer to Merged-Layer Regimes of Rarefied Flow

A Low-Load Three-Component Force Balance for Measurements in a Low-Density Wind Tunnel

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