Plug nozzles: summary of flow features and engine performance - Overview of RTO/AVT WG 10 subgroup 1

Onofri, Marcello; Calabro, Max; Hagemann, G.; Immich, H.; Sacher, Peter W.; Nasuti, Francesco; Reijasse, Philippe

doi:10.2514/6.2002-584

Cited by 39 publications

(24 citation statements)

References 28 publications

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“…However, technological difficulties in the development of the aerospike nozzle made it fall behind the development of conventional nozzle and research on the aerospike nozzle stagnated. In the 1990s, much attention was devoted to this nozzle concept and intensive studies on the aerospike nozzle were carried out again in the United States [1,2], Europe [3], Japan [4,5], Russia [6,7] and China [8]. Because of overweight composite cryogenic fuel tank and high cost, X-33 vehicle plan was called off eventually, however, full-size linear aerospike engine was produced and hot-firing tested at sea level successfully.…”

Section: Introductionmentioning

confidence: 99%

Aerospike nozzle contour design and its performance validation

2009

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Section: Introductionmentioning

confidence: 99%

Aerospike nozzle contour design and its performance validation

2009

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“…1,2 In the recent years, a renewed interest in the aerospike nozzle flowfield has been generated for both rocket and aeronautic applications. [2][3][4][5][6] However, while flow separation in over-expanded planar or bell ideal and optimized contour nozzles has been widely investigated to elucidate the phenomenon of boundary layer separation and shock interactions, aerospike nozzles have received little attention in the frame of this study. Verma 4 and Kapilavai et al 7 presented pioneering work upon flow separation behavior in aerospike nozzles that operated at NPRs below 10, and both of the two studies indicated that the presence of flow phenomenon was associated with nozzle flow separation, and unsteady shock oscillation induced by the interaction of the shock/boundary layer seen in conventional supersonic nozzles with diverging sections could also be expected in aerospike nozzles at off-design operating NPRs.…”

Section: Introductionmentioning

confidence: 99%

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

Miaosheng

Li-zi

Liu

2015

Chinese Journal of Aeronautics

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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 included. The 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 complex. An 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 observed. The 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 nozzle. Correlation of flow separation with the gas density is distinct for highly overexpanded conditions. Decreasing 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 behavior. The 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.

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“…Several studies point out these benefits in detail 17,23 and discuss proper flow expansion of an aerospike. 19,22 The self-adjusting feature of an aerospike engine only occurs at altitudes below the engine design altitude. Above this point, the engine performs similar to a conventional bell nozzle, which is why an aerospike engine should be designed with a design altitude as high as possible.…”

Section: Introductionmentioning

confidence: 99%

Advanced Design of a Multi-Thruster LOX/Propylene Aerospike Engine

Meiss

Besnard

2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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The paper presents the design of a 30kN multi-thruster annular aerospike engine as candidate for the first stage of a two-stage pressure-fed Nanosat Launch Vehicle (NLV). Detailed description of the injector and layout of single thruster are provided. A major enhancement compared to a classical multi-chamber design with straight thrusters is achieved by introducing nozzle curvature in the circumferential and in the longitudinal direction. This approach allows increasing the available exit area, or pressure ratio, thus improving performance. The design work is supported by numerical analyses of the flow inside the curved thrusters and along the engine including slipstream effects using Reynolds-Averaged Navier-Stokes simulations with realizable k-ε turbulence modeling. The computations indicate an improved performance of the dual curved thrusters engine, which is about 2% above the linear design and above an ideal bell nozzle of equal area ratio. Simultaneously, the use of a larger expansion ratio reduces base drag in the transonic flight regime.

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Plug nozzles: summary of flow features and engine performance - Overview of RTO/AVT WG 10 subgroup 1

Cited by 39 publications

References 28 publications

Aerospike nozzle contour design and its performance validation

Aerospike nozzle contour design and its performance validation

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

Advanced Design of a Multi-Thruster LOX/Propylene Aerospike Engine

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