Flow over an all-body hypersonic aircraft - Experiment and computation

Lockman, W. K.; Lawrence, Scott L.; Cleary, J. W.

doi:10.2514/3.26308

Cited by 25 publications

(4 citation statements)

References 6 publications

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“…The grid is divided using ICEM CFD, and Figure 8 shows the grid of the vehicle with the wings deployed. To ensure the accuracy of the numerical simulation, validation of the turbulence model was conducted using the Ames all-body model from NASA's Ames Research Center [34]. This model has undergone comprehensive wind tunnel testing, and currently serves as a standard for validating turbulence models in the majority of hypersonic vehicle CFD research efforts.…”

Section: Numerical Simulation 31 Settingsmentioning

confidence: 99%

Parametric Design Method and Lift/Drag Characteristics Analysis for a Wide-Range, Wing-Morphing Glide Vehicle

Jin,

Yu,

Meng

et al. 2024

Aerospace

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The parametric design method is widely utilized in the preliminary design stage for hypersonic vehicles; it ensures the fast iteration of configuration, generation, and optimization. This study proposes a novel parametric method for a wide-range, wing-morphing glide vehicle. The whole configuration, including a waverider fuselage, a rotating wing, a blunt leading edge, rudders, etc., can be easily described using 27 key parameters. In contrast to the typical parametric method, the new method takes internal payloads into consideration during the shape optimization process. That is, the vehicle configuration can be flexibly adjusted depending on the internal payloads; these payloads may be of random amounts and have different shapes. The code for the new parametric design method is developed using the secondary development tools of UG (UG 10.0) commercial software. The lift and drag characteristics over a wide operational range (H = 6–25 km, M = 2.5–8.5, AOA = 0–10°) were numerically investigated, as was the influence of the retracting angle of the morphing wings. It was found that, for the mode of the fully deployed wings, the lift-to-drag ratio (L/D) remained at a high level (≥4.7) over a Mach range of 4.0–8.5 and an AOA range of 4–7°. For the mode of the fully retracted wings, the drag coefficient remained smaller than 0.02 over a Mach range of 4.0–8.5 and an AOA range of 0–5°. A wide L/D of 0.3–4.7 could be achieved by controlling the retracting angle of the wings, thus demonstrating a good potential for flight maneuverability. The flexible change in L/D proved to be a combined result of varying pressure distribution and edge-flow spillage. This will aid in the further optimization of lift/drag characteristics.

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Section: Numerical Simulation 31 Settingsmentioning

confidence: 99%

Parametric Design Method and Lift/Drag Characteristics Analysis for a Wide-Range, Wing-Morphing Glide Vehicle

Jin,

Yu,

Meng

et al. 2024

Aerospace

View full text Add to dashboard Cite

show abstract

“…Grid Size 𝐂𝐂 𝐋𝐋 𝐂𝐂 𝐃𝐃 The CFD code used herein was validated against the experimental results of an allbody hypersonic aircraft [21]. The experimental conditions were as follows: M ∞ = 7.4, Re ∞ = 15 × 10 6 , T ∞ = 62K, T w = 300K, and α = 0 • , 5 • , 10 • , and 15 • .…”

Section: Casesmentioning

confidence: 99%

A Novel Direct Optimization Framework for Hypersonic Waverider Inverse Design Methods

Son

Yee

2022

Aerospace

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Waverider is a hypersonic vehicle that improves the lift-to-drag ratio using the shockwave attached to the leading edge of the lifting surface. Owing to its superior aerodynamic performance, it exhibits a viable external configuration in hypersonic flight conditions. Most of the existing studies on waverider employ the inverse design method to generate vehicle configuration. However, the waverider inverse design method exhibits two limitations; inaccurate definition of design space and unfeasible performance estimation during the design process. To address these issues, a novel framework to directly optimize the waverider is proposed in this paper. The osculating cone theory is adopted as a waverider inverse design method. A general methodology to define the design space is suggested by analyzing the design curves of the osculating cone theory. The performance of the waverider is estimated accurately and rapidly via combining a high-fidelity computational fluid dynamics solver and a surrogate model. A comparison study shows that the proposed direct optimization framework enables a more accurate design space and efficient performance estimation. The framework is applied to the multi-objective optimization problem, which maximizes internal volume and minimizes aerodynamic drag. Finally, general characteristics for waverider are presented by analyzing the optimized results with data mining methods such as K-means.

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“…The all-body hypersonic model is utilized to verify the precision of the aerodynamic model used in this paper. 42 The flow conditions of test are: Ma ¼ 7:4, R e ¼ 1:5e7, and AOA 2 0 , 5 , 15…”

Section: Aerodynamic Model and Its Validationmentioning

confidence: 99%

Hypersonic lifting body aerodynamic shape optimization based on the multiobjective evolutionary algorithm based on decomposition

Yang

Feng

et al. 2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this work, a volume and longitudinal stability-constrained multiobjective aerodynamic shape optimization is conducted. The aerodynamic shapes of lifting bodies are parameterized by using class function/shape function transformation parameterization method for maximum design flexibility. Hypersonic aerodynamic objectives and constraints are analyzed by solving the Reynolds-averaged Navier-Stokes equations in conjunction with a two-equation turbulence model. The Kriging technique is adopted to construct surrogate models aiming at reducing the computational cost. A two-stage method of infill sampling combined with multiobjective optimization is proposed to improve the performance of the surrogate models. Multiobjective evolutionary algorithm based on decomposition (MOEA/D) combined with penalty function method is employed to handle the multiobjective optimization problem with nonlinear constraints. The optimization results reveal that the two-stage method based on surrogates can reduce the computational cost significantly, and the accuracy of the surrogates around the Pareto front is sufficient. The two objectives are competing such that a set of Pareto optimal solutions are obtained, which are the best tradeoffs among the objectives. The unconstrained multiobjective optimization problem is also investigated with MOEA/D and nondominated sorting genetic algorithm II (NSGA-II) respectively to make a further comparison. The results show that the Pareto sets based on MOEA/D are more excellent and distribute more evenly than that obtained by NSGA-II. The computational efficiency of MOEA/D is about six times faster than that of NSGA-II. Lastly, aerodynamic characters of typical shape of Pareto front are analyzed under different flight conditions, and the results reveal favorable robustness of this shape.

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Flow over an all-body hypersonic aircraft - Experiment and computation

Cited by 25 publications

References 6 publications

Parametric Design Method and Lift/Drag Characteristics Analysis for a Wide-Range, Wing-Morphing Glide Vehicle

Parametric Design Method and Lift/Drag Characteristics Analysis for a Wide-Range, Wing-Morphing Glide Vehicle

A Novel Direct Optimization Framework for Hypersonic Waverider Inverse Design Methods

Hypersonic lifting body aerodynamic shape optimization based on the multiobjective evolutionary algorithm based on decomposition

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