Development of square nozzles for supersonic low-disturbance wind tunnels

Alcenius, Timothy J.; Schneider, Steven P.; Beckwith, I. E.; White, J. A.; Korte, John J.

doi:10.2514/3.47067

Cited by 10 publications

(6 citation statements)

References 19 publications

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“…The new nozzle has a throat curvature radius to throat radius ratio of 6 as in the sample nozzle design of Sivells [21] and as in the nozzle designed by Adams [24]. It is also close to the values of 5 and 6.6 used in [25]. This follows the recommendation by Sivells reported in [23] to use a large value for this parameter for flow quality, this value to be greater than 1 for accurate machining.…”

Section: Nozzle Designsupporting

confidence: 63%

“…The goal is to improve the conventional nozzle geometry to produce higher quality flow at the same nozzle inflow conditions. The design of the new nozzle is obtained by using the code developed by Alcenius and Schneider [20] in conjunction with the CONTUR code [21]. The code of Alcenius and Schneider, used for the convergent part, is based on the Hopkins and Hill [22] perturbation solution for the flow in the transonic region of an axisymmetric nozzle.…”

Section: Nozzle Designmentioning

confidence: 99%

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A contoured nozzle design method for effective cold spray metal coating

Zavalan

Rona

2021

ICLASS

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In cold spraying, a uniform particle distribution of uniform velocity is desirable to achieve a good quality deposition pattern. Whereas many cold spray facilities use conical convergentdivergent nozzles for accelerating the particles, this paper evaluates a contoured axisymmetric nozzle design to enhance the process efficiency. The performance of a conventional conical cold spray nozzle is compared with that of a new axisymmetric nozzle designed with a smooth throat and contoured for a parallel outflow. The new nozzle profile is obtained by the application of two aerospace design codes based on the Method of Characteristics. A two-way coupled Eulerian-Lagrangian Computational Fluid Dynamics formulation is used, where the continuous phase steady motion is predicted by solving the Reynolds-Averaged Navier-Stokes equations with the Shear Stress Transport k-ω model. A Discrete Phase Model computes the motion of the particles carried by the jet. The numerical predictions show that the new nozzle shape delivers a more radially uniform deposition. A higher particle velocity is also obtained at the same operating conditions used by the industry standard nozzle, which is desirable for good particle bonding to the substrate.

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Section: Nozzle Designsupporting

confidence: 63%

Section: Nozzle Designmentioning

confidence: 99%

A contoured nozzle design method for effective cold spray metal coating

Zavalan

Rona

2021

ICLASS

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“…The bleed slot lip ahead of the throat is computed using the Hopkins-Hill technique, just as it has been at Langley, except a new, documented version was written [3]. The suction side of the bleed slot lip has been designed by the method of streamtubes, as was done by Beckwith [2]. The design of the contraction and bleed-slot area will be described together with the mechanical design in Reference [56].…”

Section: Summary Of Design Methodsmentioning

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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“…As supersonic wind tunnel nozzle design is the objective, therefore, 2D design with two side walls parallel to each other and two curved walls in upper and lower sides of the nozzle geometry is considered for this study and has been used in several other studies including Refs. [6,12]. A 3D type nozzle design is mostly used for the design of hypersonic wind tunnels [13].…”

Section: Review Of the Theoretical Fundamentalsmentioning

confidence: 99%

A simplified design approach for high-speed wind tunnels. Part I: Table of inclination

et al. 2020

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This study aims to develop a simplified approach for the design of high-speed wind tunnels, operating within the range of Mach 1-4. The study is conducted in two stages; design stage-I consists of the basic parts of a high-speed wind tunnel, i.e. test section and nozzle throat sizes along with the calculations of the minimum pressure ratios necessary for the starting and running of the wind tunnel. Design stage-II is the aerodynamic design of the inlet nozzle contour with the focus on the divergent nozzle section only. In this stage, the fundamental method of characteristics (MOC) is employed by using region-to-region solution approach. Due to the long and complicated procedure of classical MOC, a simpler approach of "table of inclination" is proposed. This inclination table approach is simple in use, highly precise, and efficient which reduces more than 75 % of the calculation time of the MOC. Validation of the nozzle contour design is performed with the Area-Mach ratio relation followed by the results verification obtained from the MATLAB programming. The contour design results of the study are highly accurate (less than 1 % error) which manifests the future possible significance of the inclination table approach for supersonic wind tunnel designs.

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Development of square nozzles for supersonic low-disturbance wind tunnels

Cited by 10 publications

References 19 publications

A contoured nozzle design method for effective cold spray metal coating

A contoured nozzle design method for effective cold spray metal coating

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

A simplified design approach for high-speed wind tunnels. Part I: Table of inclination

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