Airbreathing hypersonic vehicle design and analysis methods and interactions

Lockwood, Mary Kae; Petley, D. H.; Martín, José Manuel Sánchez; Hunt, J. L.

doi:10.1016/s0376-0421(98)00008-6

Cited by 29 publications

(11 citation statements)

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“…[1][2][3] The main challenging issues include: aerodynamic characteristics, 4,5 scramjet-powered propulsion system, [6][7][8] and aeroelastic characteristics. 10,11 Several programs have been developed for integrated design, analysis, and optimization of hypersonic vehicles, such as the Aerospace Vehicles Simulation and Analysis Program for Hypersonics (ASAP-Hypersonics), 12 the Integrated Design & Engineering Analysis (IDEA), 13 the HOLIST, 14 the Michigan-Air Force Scramjet In Vehicle (MASIV) 8 and so on. With the advance of modern aerospace systems, the major challenges have come to the formulation of the efficient high-fidelity model for engineering full-scale analysis and optimization.…”

Section: Introductionmentioning

confidence: 99%

Surrogate modeling of a 3D scramjet-powered hypersonic vehicle based on screening method IFFD

Chen

Liu

Shen

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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The emphasis of this paper lies in the development of an efficient approach to reproduce the behaviors of the scramjetpowered hypersonic system with high fidelity. The modeling of the dual-mode scramjet powered hypersonic vehicle dynamics with shock interaction, Ram-to-Scram transition, and finite rate chemistry reaction is firstly introduced. The structure of surrogate model is identified with the implement of iterative fractional factorial design (IFFD). In order to declare the reliability of the surrogate models, -gap metric is applied to distinguish the difference among these surrogate models in terms of closed-loop performance. The results show that the influence of Mach number on the aerodynamics should not be overlooked, and the effect of propulsion system to the aerodynamic pitch moment is dramatic. Further, the partial Kriging model appears to have the closest plants throughout the flight envelope compared with the full Kriging model and polynomials model. Nevertheless, considering the briefness of analytical expression, the polynomials model may be an alternative approach for design-oriented modeling.

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Section: Introductionmentioning

confidence: 99%

Surrogate modeling of a 3D scramjet-powered hypersonic vehicle based on screening method IFFD

Chen

Liu

Shen

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…The coupling between the fuselage and propulsion system is a key technology for the development of air-breathing hypersonic vehicles. The simulation of the integrated flow characteristics of internal and external flows determines the accuracy of the aerodynamic characteristics of air-breathing aircraft (Lockwood et al, 1999;Yelan, Yang et al 2015 and Huang and Wang, 2009). Numerical simulation is the main method used to obtain the aerodynamic characteristics of air-breathing aircraft, and plays a crucial role in the conceptual design stage.…”

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confidence: 99%

Assessment of Numerical Method by Experimental Data for Integrated Hypersonic Vehicles

Wen

Liu

et al. 2019

JAFM

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This paper addresses the problem of rapid aerodynamic assessment and experimental verification of integrated hypersonic vehicles. Based on the adaptive Cartesian grid system, the aerodynamic performance of the air-breathing hypersonic vehicle is evaluated. Corresponding shrunken experimental model is investigated in FL-28 transient hypersonic wind tunnel. The grid-independent validation confirmes the proposed meshing method and optimal grid parameters. The convergent method is used for the aircraft model to calculate several flight conditions in cold state, and the calculated results are compared with the wind tunnel test data. The results show that in order to validate the accurate non-viscous dynamic characteristics of both internal and external flows, it is necessary to locally encrypt the grids of inner flow channel while ensuring the overall grid density of the aircraft. Although the computational time increases after grid encryption, the rapid prediction method of aerodynamic performance meets the requirements for engineering design. Compared with experimental results, there are several shockwave features invisible in the numerical results due to the simplification of solution procedure. The aerodynamic force coefficients obtained by the numerical method are verified by the experimental data and the same numerical method can be used in the conceptual design phase of aerodynamic shapes, which can greatly shorten the development cycle.

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“…A hypersonic flight experimental vehicle, Hyflex, was designed, developed, and flight tested [6] in 1996 as the precursor engineering demonstrator of the H-II Orbiting Plane program of Japan. Computational fluid dynamics (CFD) tools were used extensively for the design and analysis of various subsystems in hypersonic flight regime, like laminar/turbulent transition on forebody [7], aerothermodynamics [8], surface heating [9], scramjet combustor [10], etc. Complete vehicle analysis integrating both external and internal flow together is scarce.…”

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confidence: 99%

Computational Fluid Dynamics Simulation of Tip-to-Tail for Hypersonic Test Vehicle

Dharavath

Manna

Chakraborty

2015

Journal of Propulsion and Power

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Computational fluid dynamics simulations are carried out for a complete hypersonic vehicle integrating both external (nonreacting) and internal (reacting) flow together to calculate the scramjet combustor performance and vehicle net thrust minus drag. Simulations are carried out for a flight Mach number of about six. Three-dimensional Navier-Stokes equations are solved along with the shear stress transport k-ω turbulence model and single-step chemical reaction based on fast chemistry. The Lagrangian particle tracking method for droplets is used for combustion of kerosene fuel. Flow is largely nonuniform at the inlet of the combustor. Mass flow of ingested air increases with increase in angle of attack. Because of more combustion of fuel, wall surface pressure is higher for α 6 deg compared with α 0 deg. Combustion efficiency and thrust achieved are found to increase with the increase in angle of attack. Considerable amount of thrust is obtained from a single expansion ram nozzle and achievement of positive thrust-drag for the whole vehicle is demonstrated. The computational analysis of the whole vehicle provides net forces and moments of the whole vehicle, which is very useful for the mission analysis of the vehicle. NomenclatureA ebu , B ebu = model coefficient of eddy dissipation model D = Rosin Rammler diameter F = blending function, factor of safety in grid convergence index, thrust f = parameter of grid convergence index H = enthalpy, altitude h = height of cruise vehicle, grid spacing I = species component, specific impulse i, j, k = three axes direction k = turbulent kinetic energy M = molecular weight, Mach number m = flow rate P = pressure Pr = Prandtl number p = order of accuracy in grid convergence index q = heat flux R k = mixing rate of eddy dissipation model S = source term T = temperature t = time x, y, z = three axes direction Y = species mass fraction α = angle of attack η = efficiency μ = viscosity ν = dispersion factor, stoichiometric coefficient, kinematic viscosity ρ = density τ = shear stress ϕ = equivalence ratio Ω = strain rate ω = turbulent frequency Subscripts a = air ci = combustor inlet CV = cruise vehicle f = fuel i = various species k = x, y, z directions L = lift o = oxidizer p = product rec = recovery SERN = single expansion ramp nozzle t = turbulent 0 = total 1, 2 = fine, coarse grid ∞ = freestream

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Airbreathing hypersonic vehicle design and analysis methods and interactions

Cited by 29 publications

References 0 publications

Surrogate modeling of a 3D scramjet-powered hypersonic vehicle based on screening method IFFD

Surrogate modeling of a 3D scramjet-powered hypersonic vehicle based on screening method IFFD

Assessment of Numerical Method by Experimental Data for Integrated Hypersonic Vehicles

Computational Fluid Dynamics Simulation of Tip-to-Tail for Hypersonic Test Vehicle

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