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Numerical investigation of flow separation behavior in an over-expanded annular conical aerospike nozzle

Chinese Journal of Aeronautics 2015年第4期28卷 983-1002页

作者： He Miaosheng Qin Lizi Liu Yu School of Astronautics Beihang University

A three-part numerical investigation has been conducted in order to identify the flow separation behavior––the progression of the shock structure, the flow separation pattern with an increase in the nozzle pressure ratio（NPR）, the prediction of the separation data on the nozzle wall,and the influence of the gas density effect on the flow separation behavior are *** computational results reveal that the annular conical aerospike nozzle is dominated by shock/shock and shock/boundary layer interactions at all calculated NPRs, and the shock physics and associated flow separation behavior are quite *** abnormal flow separation behavior as well as a transition process from no flow separation at highly over-expanded conditions to a restricted shock separation and finally to a free shock separation even at the deign condition can be *** complex shock physics has further influence on the separation data on both the spike and cowl walls, and separation criteria suggested by literatures developed from separation data in conical or bell-type rocket nozzles fail at the prediction of flow separation behavior in the present asymmetric supersonic *** of flow separation with the gas density is distinct for highly overexpanded *** the gas density or reducing mass flow results in a smaller adverse pressure gradient across the separation shock or a weaker shock system, and this is strongly coupled with the flow separation *** computational results agree well with the experimental data in both shock physics and static wall pressure distribution at the specific NPRs, indicating that the computational methodology here is advisable to accurately predict the flow physics.

关键词： Aerodynamics aerospike nozzle Flow simulation Flow separation Gas density effect Over-expanded flow Reynolds-averaged Navier-Stokes (RANS)

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Computational Study of Performance Characteristics for Truncated Conical aerospike nozzles

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Journal of Thermal Science 2017年第6期26卷 483-489页

作者： Prasanth P Nair Abhilash Suryan Heuy Dong Kim Department of Mechanical Engineering College of Engineering Trivandrum Department of Mechanical Engineering Andong National University

aerospike nozzles are advanced rocket nozzles that can maintain its aerodynamic efficiency over a wide range of altitudes. It belongs to class of altitude compensating nozzles. A vehicle with an aerospike nozzle uses less fuel at low altitudes due to its altitude adaptability, where most missions have the greatest need for thrust. aerospike nozzles are better suited to Single Stage to Orbit （SSTO） missions compared to conventional nozzles. In the cur- rent study, the flow through 20% and 40% aerospike nozzle is analyzed in detail using computational fluid dy- namics technique. Steady state analysis with implicit formulation is carried out. Reynolds averaged Navier-Stokes equations are solved with the Spalart-AUmaras turbulence model. The results are compared with experimental results from previous work. The transition from open wake to closed wake happens in lower nozzle Pressure Ratio for 20% as compared to 40% aerospike nozzle.

关键词： aerospike nozzle plug nozzle advanced rocket nozzles thrust coefficient base pressure.

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Studies on Aerodynamic Behavior and Performance of aerospike nozzles

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Chinese Journal of Aeronautics 2006年第1期19卷 1-9页

作者：王长辉刘宇廖云飞 School of Astronautics Beijing University of Aeronautics and Astronautics Beijing 100083 China

Experimental and numerical studies are carried out on a 6-cell tile-shaped aerospike nozzle, a 6-cell aerospike nozzle with round-to-rectangle primary nozzles and a 1-cell linear aerospike nozzle. Good altitude compensation capacities and high efficiencies are obtained in the tests. The efficiencies of 6-cell tile-shaped aerospike nozzle and 1-cell linear aerospike nozzle at design altitude approach to 100 %, and that of 6-cell aerospike nozzle with round-to-rectangle primary nozzles in the same condition is about 95 % due to the imperfect cell contour and manufacturing defects. Numerical results are in good agreements with test data. The effects of ambient pressure on exhaust and then on base behavior are analyzed, The effects of variation in the amount of base bleed on performance are also examined in the tests.

关键词： rocket engine aerospike nozzle performance experiment numerical simulation

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Computational study on flow through truncated conical plug nozzle with base bleed

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Propulsion and Power Research 2019年第2期8卷 108-120页

作者： Prasanth P.Nair Abhilash Suryan Heuy Dong Kim Department of Mechanical Engineering College of Engineering TrivandrumTrivandrum 695016India Department of Mechanical Engineering Andong National UniversityAndong 760749Republic of Korea

Conical plug nozzle and truncated conical plug nozzle are advanced rocket nozzles suitable for use as altitude compensating *** this study flow through the conical plug and truncated conical plug nozzles are numerically simulated to first validate with experimental data and then to compare the performance when a base bleed is *** numerical analysis has considered two-dimensional axisymmetric ***-averaged NavierStokes equations are solved with two equation shear stress transport k-ω turbulence *** the validation of the plug nozzle,flow features and wall pressure along the length of the nozzle is taken for different nozzle pressure *** the validation of truncated plug nozzle,flow features and base pressures at various nozzle pressure ratios are *** base bleed is taken as 2%of the inlet mass flow *** comparison of results shows that the introduction of base bleed helps to compensate for the loss of thrust due to conical plug nozzle truncation.

关键词： Plug nozzle aerospike nozzle Advanced rocket nozzle Reynolds-averaged Navier-Stokes(RANS) Base pressure Coefficient of thrust Base bleed Secondary flow

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