A Study of the Nozzle Flow in a Large Arc-Heated Hypersonic Wind Tunnel PDF Download
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Author: James T. Van Kuren
Publisher:
ISBN:
Category :
Languages : en
Pages : 139
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Book Description
The objective of the study was to obtain information about the flow of chemically reacting air that has been heated in a vortex stabilized, high voltage, direct current arc and expanded to hypersonic speeds in a conical nozzle. The inviscid core of the axisymmetric flow in the supersonic section of the nozzle was theoretically analyzed by the method of characteristics for air in chemical and thermal equilibrium. Impact pressure, mass flux, and heat transfer profiles and nozzle-wall static pressures were obtained. Light emissions from the reacting stream were recorded spectroscopically. (Modified author abstract).
Author: James T. Van Kuren
Publisher:
ISBN:
Category :
Languages : en
Pages : 139
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Book Description
The objective of the study was to obtain information about the flow of chemically reacting air that has been heated in a vortex stabilized, high voltage, direct current arc and expanded to hypersonic speeds in a conical nozzle. The inviscid core of the axisymmetric flow in the supersonic section of the nozzle was theoretically analyzed by the method of characteristics for air in chemical and thermal equilibrium. Impact pressure, mass flux, and heat transfer profiles and nozzle-wall static pressures were obtained. Light emissions from the reacting stream were recorded spectroscopically. (Modified author abstract).
Author: James Thomas Van Kuren
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 410
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Book Description
Author: John B. Anders
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 36
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Book Description
A hypersonic-wind-tunnel nozzle concept which incorporates a hot-core flow surrounded by an annular flow of cold air offers a promising technique for maximizing the model size while minimizing the power required to heat the test core. This capability becomes especially important when providing the true-temperature duplication needed for hypersonic propulsion testing. Several two-dimensional wind-tunnel nozzle configurations that are designed according to this concept are analyzed by using recently developed analytical techniques for prediction of the boundary-layer growth and the mixing between the hot and cold coaxial supersonic airflows. The analyses indicate that introduction of the cold annular flow near the throat results in an unacceptable test core for the nozzle size and stagnation conditions considered because of both mixing and condensation effects. Use of a half-nozzle with a ramp on the flat portion does not appear promising because of the thick boundary layer associated with the extra length. However, the analyses indicate that if the cold annular flow is introduced at the exit of a full two-dimensional nozzle, an acceptable test core will be produced. Predictions of the mixing between the hot and cold supersonic streams for this configuration show that mixing effects from the cold flow do not appreciably penetrate into the hot core for the large downstream distances of interest.
Author: Roger Bell Stewart
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 40
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Author: Ruth N. Weitmann
Publisher:
ISBN:
Category : Chemistry, Physical and theoretical
Languages : en
Pages : 36
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Author: P.M. Sherman
Publisher:
ISBN:
Category :
Languages : en
Pages : 198
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Book Description
Author: James L. Folck
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 162
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Book Description
Author: Thomas Laurence Larsen
Publisher:
ISBN:
Category :
Languages : en
Pages : 81
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Book Description
The study experimentally investigated equilibrium and non-equilibrium flow at the exit of a 9 1/2 inch diameter axisymmetric contoured hypersonic nozzle. The flow was probed with an impact pressure probe, and steady state and transient calorimeters, and the velocity was calculated from these data. The shape of the resulting velocity profiles showed that the nozzle produced uniform parallel flow, and that the nozzle design method was adequate for use in designing a 5.5 foot diameter contoured nozzle to produce equilibrium flow up to Mach 10 and non-equilibrium flow at Mach numbers of 11-15 in an arc-heated hypersonic tunnel. (Author).
Author: Martin Sichel
Publisher:
ISBN:
Category :
Languages : en
Pages : 84
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Book Description
Author: William B. Boatright
Publisher:
ISBN:
Category : Wind tunnels
Languages : en
Pages : 44
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Book Description
