Доступ предоставлен для: Guest
Главная ICHMT DL Текущий год Архив Исполнительный Комитет ICHMT

Estimation of Flow Field Properties and Thrust Performances of Axisymmetric Plug - Nozzles using CFD Simulations

DOI: 10.1615/ICHMT.2009.TurbulHeatMassTransf.700
page 13

Ognjan Bozic
DLR – Institute of Aerodynamics and Flow Technology(AS), Lilienthalplatz 7, D- 38108 Braunschweig, Germany

Dennis Porrmann
DLR – Institute of Aerodynamics and Flow Technology(AS), Lilienthalplatz 7, D- 38108 Braunschweig, Germany


The objective of the presented work is to investigate the slipstream effects on the flow properties and thrust performances of a full-length and truncated annular plug nozzle of a small rocket launcher during a suborbital flight. The nozzle flow properties are investigated for three characteristics flow conditions (M = 1.3, 2.59 and 9.7), using CFD simulations. When the rocket launcher flies through the atmosphere, the body geometry produces a slipstream with conditions in the nozzle area that are different from the undisturbed environment. The in-flight behavior of the truncated plug nozzles is complicated and affected also by recirculation regions that take place behind the shroud and plug base. In this paper special emphasis is given to investigate the slipstream effects between the hot exhaust plume from the rocket engine and the external coaxial supersonic/hypersonic air flow and their influence on the slope and position of different shocks generated in the separated flow region (realignment shocks, recompression shocks, plug base lip shock and trailing shocks). Also analyzed is the pressure distribution on the shroud base, spike supersonic ramp and spike base for closed-wake operations to determine the overall engine performance. The results of the numerical simulations confirm the altitude-compensating features of the annular truncated plug nozzles.

ICHMT Digital Library

Bow shocks on a jet-like solid body shape. Thermal Sciences 2004, 2004. Pulsed, supersonic fuel jets - their characteristics and potential for improved diesel engine injection. PULSED, SUPERSONIC FUEL JETS - THEIR CHARACTERISTICS AND POTENTIAL FOR IMPROVED DIESEL ENGINE INJECTION
View of engine compartment components (left). Plots of temperature distributions in centreplane, forward of engine (right). CHT-04 - Advances in Computational Heat Transfer III, 2004. Devel... DEVELOPMENT AND CURRENT STATUS OF INDUSTRIAL THERMOFLUIDS CFD ANALYSIS
Pratt & Whitney's F-135 Joint Strike Fighter Engine under test in Florida is a 3600F class jet engine. TURBINE-09, 2009. Turbine airfoil leading edge stagnation aerodynamics and heat transfe... TURBINE AIRFOIL LEADING EDGE STAGNATION AERODYNAMICS AND HEAT TRANSFER - A REVIEW
Refractive index reconstructed field. (a) Second iteration. (b) Fourth iteration. Radiative Transfer - VI, 2010. Theoretical development for refractive index reconstruction from a radiative ... THEORETICAL DEVELOPMENT FOR REFRACTIVE INDEX RECONSTRUCTION FROM A RADIATIVE TRANSFER EQUATION-BASED ALGORITHM
Two inclusion test, four collimated sources. Radiative Transfer - VI, 2010. New developments in frequency domain optical tomography. Part II. Application with a L-BFGS associated to an inexa... NEW DEVELOPMENTS IN FREQUENCY DOMAIN OPTICAL TOMOGRAPHY. PART II. APPLICATION WITH A L-BFGS ASSOCIATED TO AN INEXACT LINE SEARCH