Flow Separation in Rocket Nozzles, a Simple Criteria

Stark, Ralf

doi:10.2514/6.2005-3940

Cited by 32 publications

(23 citation statements)

References 16 publications

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“…A comparison of the current separation location with a selected number of separation criteria [51,36,41,40] is given in figure 4. Note that we measured the separation point location using oil flow visualization.…”

Section: Mean Flow Fieldmentioning

confidence: 99%

Wall Pressure and External Velocity Field Relation in Overexpanded Supersonic Jets

et al. 2017

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Section: Mean Flow Fieldmentioning

confidence: 99%

Wall Pressure and External Velocity Field Relation in Overexpanded Supersonic Jets

et al. 2017

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“…To assess the influence of modeled turbulence in the flow field, the SA model was compared to the -shear stress transport model [25] ( -SST) and the -realizable model [26] ( -), both of which have been used in previous work to model similar flow fields [27]. In addition to varying the turbulence model, an inviscid solution was compared to assess the influence of turbulence itself within the flow field.…”

Section: Turbulence Modellingmentioning

confidence: 99%

“…Theoretically, flow separation should be avoided when either nozzle operates under general OX conditions [9]. However, it is important to note that the inherent instability of flow separation makes accurate prediction difficult [11] and that the purely empirical Summerfield's criterion [9] is unable to account for the amplification of boundary layer aggravation present in low Mach number flows [27]. The measured stagnation pressures were 6.33 and 6.46 atm in the CD and ED configurations, respectively.…”

Section: Overexpanded (Ox) Conditionmentioning

confidence: 99%

Analysis of a Low-Angle Annular Expander Nozzle

Schomberg

Olsen

Doig

2015

Shock and Vibration

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An experimental and numerical analysis of a low-angle annular expander nozzle is presented to observe the variance in shock structure within the flow field. A RANS-based axisymmetric numerical model was used to evaluate flow characteristics and the model validated using experimental pressure readings and schlieren images. Results were compared with an equivalent converging-diverging nozzle to determine the capability of the wake region in varying the effective area of a low-angle design. Comparison of schlieren images confirmed that shock closure occurred in the expander nozzle, prohibiting the wake region from affecting the area ratio. The findings show that a low angle of deflection is inherently unable to influence the effective area of an annular supersonic nozzle design.

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“…The relationship between the flow structure and NPR range is summarized in Table 1. The nozzle flow separation condition was obtained by using the criterion suggested by Stark [21]. The expansion condition is summarized in terms of the cell nozzle NPR.…”

Section: B Linear Aerospike Nozzle Configuration (Airframe External mentioning

confidence: 99%

“…Since the maximum boattail angle that limits the separation of the external flow on the boattail is not accurately known because of the viscous effects, the separation limit was determined by using the separation criterion [21] and the following relationship:…”

Section: Flight Conditionsmentioning

confidence: 99%

Performance Evaluation of Airframe-Integrated Aerospike Propulsion Systems in Off-Design Flight Conditions

Takahashi

Tomita

Tomioka

2015

53rd AIAA Aerospace Sciences Meeting

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The thrust performance of airframe-integrated linear aerospike propulsion systems for high-speed aircraft operated under off-design in-flight conditions was evaluated, based on performance prediction models established for linear aerospike nozzles by accounting for the freestream effect.The airframe configuration, equipped with a boattail appearing to the right upstream of the primary cell nozzle exit, enabled the freestream effect to be utilized for increasing the spike surface pressure.Performances of each thrust component were predicted by using the physics-based models established in separately performed studies. First, a parametric study was conducted on a rocket primary thruster with various design parameters. Then, an advanced concept with an airbreathing primary propulsion system was evaluated for its feasibility by comparing its thrust performance with that of a conventional rocket primary thruster. The benefit of the aerospike nozzle integrated into the airframe was also evaluated by comparing its thrust to a configuration without the aerospike nozzle.Results showed that the employment of the aerospike nozzle offered improved performance from takeoff to cruise phases. The advanced concept using the bypass airbreathing system for the primary thruster followed by the aerospike configuration exhibited further improvement in thrust by compensating for the boattail drag.

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Flow Separation in Rocket Nozzles, a Simple Criteria

Cited by 32 publications

References 16 publications

Wall Pressure and External Velocity Field Relation in Overexpanded Supersonic Jets

Wall Pressure and External Velocity Field Relation in Overexpanded Supersonic Jets

Analysis of a Low-Angle Annular Expander Nozzle

Performance Evaluation of Airframe-Integrated Aerospike Propulsion Systems in Off-Design Flight Conditions

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