Investigation of Two-Dimensional Wedge Exhaust Nozzles for Advanced Aircraft

Maiden, D. L.; Petit, John E.

doi:10.2514/3.58715

Journal of Aircraft

1976

DOI: 10.2514/3.58715

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Investigation of Two-Dimensional Wedge Exhaust Nozzles for Advanced Aircraft

D. L. Maiden

John E. Petit

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1985

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Investigation of flow characteristics of various-aspect-ratio rectangular nozzles with an aft deck

Chen,

Huang,

Lai

2024

Shock Waves

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This study presents an experimental and numerical investigation to characterize the plume pattern of a high-aspect-ratio rectangular convergent/divergent nozzle with an aft deck in under-expanded conditions. The function of an aft deck is to shield the infrared signal of an exhaust plume at its strongest intensity located at the immediate downstream region of the nozzle exit. However, this practice may cause undesirable plume deflection, which needs to be reduced as much as possible. The nozzle pressure ratios ranged from 2 to 4, and the effect of the nozzle exit aspect ratio was examined using wall static pressure measurements and schlieren visualization for cold flows. The experimental setup involved a 3D-printed aft deck nozzle made of acrylonitrile butadiene styrene material, which underwent surface smoothing using acetone vapor. Numerical simulations were conducted using the commercial STARCCM$$^{\mathrm {+}}$$ + software to analyze static pressure ratio variations at the aft deck. The investigation revealed that a nozzle pressure ratio of 3 induced a downward plume deflection at aspect ratio values of 6.77 and 7.54, while an increased aspect ratio of 8.35 resulted in the horizontal ejection of the plume. Moreover, at an aspect ratio of 8.35, the plume was ejected horizontally for nozzle pressure ratios ranging from 2 to 4. At a nozzle pressure ratio of 4, the flow separated from the deck without reattaching, and the plume moved horizontally with minimal deflection. The findings suggest that a combination of a high aspect ratio and sufficiently high nozzle pressure ratio can effectively reduce plume deflection.

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Investigation of flow characteristics of various-aspect-ratio rectangular nozzles with an aft deck

Chen,

Huang,

Lai

2024

Shock Waves

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Study of an asymmetric flap nozzle as a thrust-vectoring device

Chow

1985

Journal of Propulsion and Power

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The problem of isentropic flow through an asymmetric two-dimensional convergent nozzle as a thrustvectoring device has been solved by the method of hodograph transformation coupled with finite-difference computation. With the given appropriate flow parameters, the solution was first established in the hodograph domain. The corresponding nozzle configuration and the flowfield properties were subsequently obtained through direct integration. The thrust-vectoring performance corresponding to specific nozzle geometries were also determined and presented. Experiments for specific nozzle configurations were also conducted to obtain pressure data along the nozzle walls for verification purposes. The numerical results were found to be in good agreement with the experimental data. Nomenclatureof approaching uniform flow h E -thickness of asymtoptic uniform flow M = Mach number M* = Mach number based on critical sound speed p = pressure q = transformed velocity s = distance along nozzle wall T -thrust force V = velocity magnitude x,y = physical coordinates MU^L = upper and lower flap angles J3 -dimensionless flow angle 7 = specific heat ratio d = thrust angle 0 = flow angle p = density = potential function i/' = stream function a; = dimensionless velocity Subscripts A E E 0 = approaching uniform flow -asymtoptic uniform flow (for subcritical flow) = critical point on sonic line (for supercritical flow) = stagnation condition = freestream condition

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Investigation of Two-Dimensional Wedge Exhaust Nozzles for Advanced Aircraft

Cited by 2 publications

References 1 publication

Investigation of flow characteristics of various-aspect-ratio rectangular nozzles with an aft deck

Investigation of flow characteristics of various-aspect-ratio rectangular nozzles with an aft deck

Study of an asymmetric flap nozzle as a thrust-vectoring device

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