Design of hypersonic forebody with submerged bump

Saheby, Eiman B.; Huang, Guoping; Hays, Anthony P.

doi:10.1177/0954410018793288

Cited by 5 publications

(6 citation statements)

References 13 publications

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“…In the shock-based design method, the base-plane curve (BPC) prescribes the compression surface while the external surface should be designed based on the overall configuration of the flight vehicle. [32][33][34] A surface with BPC extends along the ramp angles until it intersects with the initial shock front. For wedge-derived surfaces, the generating flow field is defined by a two-dimensional oblique shockwave equation 32,33 tanðδÞ…”

Section: Design Of Forebody-inlet Configurationmentioning

confidence: 99%

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The inlet flow structure of a conceptual open-nose supersonic drone

Saheby

Shen

Hays

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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This study describes the aerodynamic efficiency of a forebody–inlet configuration and computational investigation of a drone system, capable of sustainable supersonic cruising at Mach 1.60. Because the whole drone configuration is formed around the induction system and the design is highly interrelated to the flow structure of forebody and inlet efficiency, analysis of this section and understanding its flow pattern is necessary before any progress in design phases. The compression surface is designed analytically using oblique shock patterns, which results in a low drag forebody. To study the concept, two inlet–forebody geometries are considered for Computational Fluid Dynamic simulation using ANSYS Fluent code. The supersonic and subsonic performance, effects of angle of attack, sideslip, and duct geometries on the propulsive efficiency of the concept are studied by solving the three-dimensional Navier–Stokes equations in structured cell domains. Comparing the results with the available data from other sources indicates that the aerodynamic efficiency of the concept is acceptable at supersonic and transonic regimes.

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Section: Design Of Forebody-inlet Configurationmentioning

confidence: 99%

“…[32][33][34] A surface with BPC extends along the ramp angles until it intersects with the initial shock front. For wedge-derived surfaces, the generating flow field is defined by a two-dimensional oblique shockwave equation 32,33 tanðδÞ…”

Section: Design Of Forebody-inlet Configurationmentioning

confidence: 99%

The inlet flow structure of a conceptual open-nose supersonic drone

Saheby

Shen

Hays

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…As a consequence, several researchers (1)(2)(3) have explored different inlet designs and identified the critical parameters to improve the airflow pressure and the overall aerodynamic features of the aircraft. Amongst these designs, the submerged inlet (also called the flush inlet) has attracted significant interest from researchers due to its unique architecture (4)(5)(6)(7)(8)(9) , especially for aircraft operating in the subsonic flow regime. Submerged inlets were first introduced in the early 1940s.…”

Section: Introductionmentioning

confidence: 99%

Design space optimisation of an unmanned aerial vehicle submerged inlet through the formulation of a data-fusion-based hybrid model

et al. 2021

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The research focuses on the design space optimisation of National Advisory Committee for Aeronautics (NACA) submerged inlets through the formulation of a hybrid data fusion methodology. Submerged inlets have drawn considerable attention owing to their potential for good on-design performance, for example during cruise flight conditions. However, complexities due to the geometrical topology and interactions among various design variables remain a challenge. This research enhances the current design knowledge of submerged inlets through the utilisation of data mining and Computational Fluid Dynamics (CFD) methodologies, focusing on design space optimisation. A two-pronged approach is employed where the first step encompasses a low-fidelity model through data mining and surrogate modelling to predict and optimise the design parameters, while the second step uses the Design of Experiments (DOE) approach based on the CFD results for the candidate design geometry to construct a surrogate model with high fidelity for design refinement. The feasibility of the proposed methodology is demonstrated for the optimisation of the total pressure recovery of a NACA submerged inlet for the subsonic flight regime. The proposed methodology is found to provide good agreement between the surrogate and CFD-based model and reduce the optimisation processing time by half in comparison with conventional (global-based) CFD optimisation approaches.

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“…The literature reports favorable characteristics of DSI in terms of pressure recovery and flow distortion at different flow speeds and angles of attack. 5,17,18 However, no information regarding the design parameters of the bump surface is available. It is still unknown whether the existing bump surfaces for DSI are optimized to provide maximum possible pressure recovery at design conditions or not.…”

Section: Introductionmentioning

confidence: 99%

Design and optimization of bump (compression surface) for diverterless supersonic inlet

Arif

Iftikhar

Javed

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this article design and optimization scheme of a three-dimensional bump surface for a supersonic aircraft is presented. A baseline bump and inlet duct with forward cowl lip is initially modeled in accordance with an existing bump configuration on a supersonic jet aircraft. Various design parameters for bump surface of diverterless supersonic inlet systems are identified, and design space is established using sensitivity analysis to identify the uncertainty associated with each design parameter by the one-factor-at-a-time approach. Subsequently, the designed configurations are selected by performing a three-level design of experiments using the Box–Behnken method and the numerical simulations. Surrogate modeling is carried out by the least square regression method to identify the fitness function, and optimization is performed using genetic algorithm based on pressure recovery as the objective function. The resultant optimized bump configuration demonstrates significant improvement in pressure recovery and flow characteristics as compared to baseline configuration at both supersonic and subsonic flow conditions and at design and off-design conditions. The proposed design and optimization methodology can be applied for optimizing the bump surface design of any diverterless supersonic inlet system for maximizing the intake performance.

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Design of hypersonic forebody with submerged bump

Cited by 5 publications

References 13 publications

The inlet flow structure of a conceptual open-nose supersonic drone

The inlet flow structure of a conceptual open-nose supersonic drone

Design space optimisation of an unmanned aerial vehicle submerged inlet through the formulation of a data-fusion-based hybrid model

Design and optimization of bump (compression surface) for diverterless supersonic inlet

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