Results 201 to 210 of about 81,739 (264)
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A Cryogenic Hypersonic Low-Density Wind Tunnel
1962In the past, hypersonic aerodynamics has been concerned primarily with continuum flow. For ballistic re-entry vehicles, it was established in earlier studies [1] that most of the problems which tend to define the vehicle occur at altitudes below 200,000 ft, where the flow is substantially a continuum one. However, lifting re-entry from satellite orbits
B. D. Henshall, E. M. Brower
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Rarefied aerodynamic measurements in hypersonic rarefied wind tunnel
AIP Conference Proceedings, 2014In order to improve the feasibility of space missions, the prediction accuracy of rarefied aerodynamics is one of the important factors. To improve rarefied aerodynamic predictions, the determination of accommodation coefficients and direct measurement of rarefied aerodynamic forces are crucial. Thus, at Japan Aerospace Exploration Agency, a hypersonic
T. Ozawa, T. Suzuki, K. Fujita
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A New Airframe/Propulsion-Integrated Aerodynamic Testing Technology in Hypersonic Wind Tunnel
IEEE Transactions on Instrumentation and Measurement, 2022Shichao Li +4 more
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Hypersonic Transition Testing in Wind Tunnels
1990Historically, the wind tunnel has been the major source of boundary-layer transition information. Often these wind tunnel data have become the primary data base used to develop transition correlations and to establish transition criteria for flight. During the late 1950’s and the 1960’s, the identification and understanding of wind tunnel freestream ...
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Nonintrusive Temperature Determination by LIF in Hypersonic Wind Tunnels
1993LIF excitation spectra of nitric oxide have been measured in a hot supersonic freejet expansion in the vacuum wind tunnel (V2G) in Goettingen to determinate rotational temperatures. To interprete the experimental results, a computer program was developed that calculates the excitation spectra for temperatures up to 2000 K.
Gundlach, G., Dankert, C.
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AIR CONDENSATION IN A HYPERSONIC WIND TUNNEL
AIAA Journal, 1963Air condensation studies were conducted in a 3-in. hypersonic wind tunnel where the flow Mach numbers ranged from 9.5 to 17.0. The stream pitot and static pressures both were found to be affected strongly by the presence of condensation. Large amounts of apparent supersaturation, which increased with increasing Mach number, were found to exist.
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A-Variant Design of Hypersonic Ludwieg Tube Wind Tunnel
AIAA Journal, 2022ZHiyuan Li +5 more
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HYPERSONIC WIND TUNNEL FACILITIES IN THE UNITED STATES
1963Abstract : Contents: Overall performance maps of wind tunnel facilities currently operational or under construction Reynolds number per foot as a function of altitude Reynolds number per foot as a function of free stream Mach number Reynolds number-Mach number-altitude chart Index of test ...
Nancy S. Foy, F. A. Vicente
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Design and Performance of a Hypersonic Wind Tunnel
Volume 1B, Symposia: Fluid Measurement and Instrumentation; Fluid Dynamics of Wind Energy; Renewable and Sustainable Energy Conversion; Energy and Process Engineering; Microfluidics and Nanofluidics; Development and Applications in Computational Fluid Dynamics; DNS/LES and Hybrid RANS/LES Methods, 2017A moveable block planar nozzle wind tunnel design from the University of Michigan in 1955 was shown with previous analysis to operate between Mach 1 and at least Mach 6.3 for mid-size test sections, with continuous variation in Mach number and accounting for limitations governed by supply temperature and pressure, liquefaction, flow rate, and flow ...
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Expert elicitation survey predicts 37% to 49% declines in wind energy costs by 2050
Nature Energy, 2021Ryan Wiser, Joseph Rand, Joachim Seel
exaly