Flow phenomena in advanced rocket nozzles - The plug nozzle

Hagemann, G.; Immich, H.; Terhardt, M.

doi:10.2514/6.1998-3522

Cited by 35 publications

(18 citation statements)

References 5 publications

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“…For the present design, the cowl lip radius was set to 3.4 in., and a design NPR of 16.5 was used. This resulted in a throat area of 72 in 2 , corresponding to that of the Mach 3.5 flight condition shown in Table 1, and an internal cowl angle of 46 degrees. Throat area variation is accomplished by translating the cowl axially.…”

Section: Isentropic Plug Nozzlementioning

confidence: 99%

Aerodynamic Design and Analysis of High Performance Nozzles for Mach 4 Accelerator Vehicles

Georgiadis

DalBello

Trefny

et al. 2006

44th AIAA Aerospace Sciences Meeting and Exhibit

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The aerodynamic design and performance analysis of two exhaust nozzles considered for use on a vehicle following an accelerating flight profile to a maximum flight speed corresponding to Mach 4.2 is presented. The vehicle operational requirements were set by the Air Vehicle Baseline Study commissioned by the Office of Naval Research. An afterburning engine cycle was assumed in the design and analysis process. The two nozzles investigated here were an axisymmetric convergent-divergent (C-D) nozzle with variable throat and exit area and an isentropic plug nozzle with variable throat area enabled by a translating outer cowl. Computational fluid dynamics was used to assist in the design process and to investigate the installed performance of the two nozzles at flight points from Mach 1.2 to Mach 4.2. For both nozzle configurations, the nozzles could not achieve perfectly expanded exit areas at the highest Mach numbers in order for the nozzle exit area to not exceed the vehicle cross sectional area. At the lower Mach numbers, the installed performance of the C-D nozzle was higher than that of the plug nozzle while at the highest Mach numbers, the performance of the two nozzles was similar. = nozzle exit radius corresponding to full expansion area y+ = wall normal coordinate θ = nozzle divergence angle Nomenclature

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Section: Isentropic Plug Nozzlementioning

confidence: 99%

Aerodynamic Design and Analysis of High Performance Nozzles for Mach 4 Accelerator Vehicles

Georgiadis

DalBello

Trefny

et al. 2006

44th AIAA Aerospace Sciences Meeting and Exhibit

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show abstract

“…For the tests the plug nozzle model "LION" (LInear Optimized InternallExternal Expansion Nozzle) of length L3 was used. The LION contour is a linear plug nozzle contour with pre-expansion based on a modified contour calculation [5]. In Figure 2, a spatial drawing of the investigated plug nozzle including the system of coordinates and the definition of the direction of torque is shown.…”

Section: Methodsmentioning

confidence: 99%

PSP Measurements on a Linear Plug Nozzle: Aerodynamic Investigations on Linear Plug Nozzle Configurations

Klein¹,

Niebergall

Sachs³

et al. 2004

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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SummaryPressure field measurements on a Linear Plug Nozzle model were conducted to evaluate the feasibility and accuracy of measurements using DLR's Pressure Sensitive Paint (PSP) system in the high-speed wind tunnel at Merkers (HWK) of TU-Dresden. A part of the nozzle surface was coated with binary PSP paint. Results show that the optical pressure measurement system with binary paint can be used in the HWK facility. In addition, the paper gives a summary of the thrust vector calculations based on measured static pressure distributions on the plug surface using thrust vector control.

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“…Сопла с центральным телом (или «тарельчатые» сопла, сопла с прямолинейной верхней стенкой) находят, в основном, применение в авиапромышленности при изготовлении реактив-ных двигателей [1][2][3][4][5]. Автором предложена еще одна область практического применения со-пел с центральным телом в качестве одного из элементов конструкции горелочных устройств в нагревательных и термических печах различного назначения [6][7][8][9].…”

unclassified

Методика Расчета Горелочных Устройств На Базе Сопла С Центральным Телом

Копцев¹

2007

Вестн. Сам. гос. техн. ун-та. Сер. Физ.-мат. науки

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Flow phenomena in advanced rocket nozzles - The plug nozzle

Cited by 35 publications

References 5 publications

Aerodynamic Design and Analysis of High Performance Nozzles for Mach 4 Accelerator Vehicles

Aerodynamic Design and Analysis of High Performance Nozzles for Mach 4 Accelerator Vehicles

PSP Measurements on a Linear Plug Nozzle: Aerodynamic Investigations on Linear Plug Nozzle Configurations

Методика Расчета Горелочных Устройств На Базе Сопла С Центральным Телом

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