Aerodynamic design of axisymmetric hypersonic wind-tunnel nozzles

Sivells, James C

doi:10.2514/3.30160

Cited by 77 publications

(12 citation statements)

References 13 publications

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“…Nozzle Shapes Figure 4 shows the inviscid contours of three nozzles designed with Sivell's code [61]. A 3rddegree axial velocity distribution was chosen in the throat region, and a 4th-degree velocity distribution was chosen in the exit region.…”

Section: E N Resultsmentioning

confidence: 99%

Design of a Mach-6 quiet-flow wind-tunnel nozzle using the e**N method for transition estimation

Schneider

1998

36th AIAA Aerospace Sciences Meeting and Exhibit

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A high Reynolds-number Mach-6 quiet-flow windtunnel nozzle has been designed for a new quietflow Ludwieg tube. The quiet-flow nozzle is designed to maintain laminar boundary layers on the nozzle walls as far downstream as possible. A very long nozzle with gentle curvature is used to reduce Görtler instability. Early transition would occur in adiabatic nozzles of this type, due to the first-mode TS instability. This is controlled with an isothermal wall temperature that is high near the throat and tapers to ambient near the exit. The crossflow instability is eliminated through use of an axisymmetric nozzle. Predictions using e N techniques suggest that a quiet-flow Reynolds number in excess of 13 million can be achieved in a 103-inch-long 9-inch-diameter prototype nozzle at 10 atm. total pressure. This performance would be about twice that of the existing Langley Mach-6 quiet-flow nozzle. A 33-foot-long 24-inch nozzle at the same pressure is predicted to have a quiet Reynolds number of more than 36 million, a value sufficient to allow reproducing many flight experiments.

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Section: E N Resultsmentioning

confidence: 99%

Design of a Mach-6 quiet-flow wind-tunnel nozzle using the e**N method for transition estimation

Schneider

1998

36th AIAA Aerospace Sciences Meeting and Exhibit

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“…The pitot tube was designed with a water-cooled structure. When the dynamic and static pressure were measured by the pitot tube, the Equations (1) and (2) were used to calculate the axial velocity of the coherent jet [18] (…”

Section: Structural Design and Validationmentioning

confidence: 99%

Effect of Lance Structure on Behavior of Coherent Jet in EAF Steelmaking Process

et al. 2020

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During the electric arc furnace steelmaking process, the coherent jet technology was widely used to protect the kinetic energy of the supersonic oxygen jet and achieve better mixing effects. Comparing with the conventional oxygen lance, the coherent lance could increase the surface area of impaction cavity, resulting in a better stirring effect and higher reaction rate. However, there was limited research about the effect of restriction structure for the coherent lance tip on the flow field characteristic of the main oxygen jet. In this research, three kinds of restriction structures have been investigated by numerical simulation and combustion experiment at room and high ambient temperature conditions. Then an optimum restriction structure would be tested in a 75 t electrical arc furnace steelmaking process to verify its metallurgical property.

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“…This distribution is obtained using a method outlined by Sivells [33], which requires the specification of the desired exit Mach number and is based on the assumption of radial flow downstream of the transonic region. The transonic throat region is treated using Kliegel and Levine's analysis [34], which allows for a curved sonic line.…”

Section: Rocket Flowpath Designmentioning

confidence: 99%

Exchange Inlet Design for Rocket-Based Combined-Cycle Engines

Etele

Waung

Cerantola

2012

Journal of Propulsion and Power

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A methodology is presented for generating an inlet containing an entrained flow surrounded by an annular flow of driving, supersonic gas. As the driving flow expands outward into an annular pattern, it maintains a circular throat area while allowing the entrained flow to be drawn toward the axisymmetric axis. The methodology accounts for both compressibility and viscous effects, and it can be scaled for a variety of operating conditions and driving gases. Designs are presented for the inlet to an example rocket-based combined-cycle engine based on both a kerosenefueled and a hydrogen-fueled rocket. Numerical results are presented, showing rocket exhaust patterns that contain uniform conditions over 75% of the annular exhaust area. The entrained air passage is also shown to have high total pressure recovery over the subsonic flight range. The predicted performance is shown to be within 10% of the numerical simulations over the range of conditions considered.

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Aerodynamic design of axisymmetric hypersonic wind-tunnel nozzles

Cited by 77 publications

References 13 publications

Design of a Mach-6 quiet-flow wind-tunnel nozzle using the e**N method for transition estimation

Design of a Mach-6 quiet-flow wind-tunnel nozzle using the e**N method for transition estimation

Effect of Lance Structure on Behavior of Coherent Jet in EAF Steelmaking Process

Exchange Inlet Design for Rocket-Based Combined-Cycle Engines

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