Investigation on high angle of attack characteristics of hypersonic space vehicle

Huang, Wei; Li, Shibin; Liu, Jun; Wang, Zhenguo

doi:10.1007/s11431-012-4760-6

Cited by 48 publications

(15 citation statements)

References 13 publications

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“…Numerical solutions are calculated by solving the three-dimensional compressible Navier-Stokes equations with the use of a second-order Total Variation Diminishing finite volume scheme for spatial discretization, a second-order implicit time marching scheme, and a realizable k − ε model that is used in the computations [36]. Table 3 shows the comparison of the cones' drag coefficients between the numerical and experimental results.…”

Section: B Code Validation and Grid Convergence Testmentioning

confidence: 99%

High-Pressure Capturing Wing Configurations

Cui

Xiao

et al. 2017

AIAA Journal

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This paper proposes a family of high-pressure capturing wing configurations that aim to improve the aerodynamic performance of hypersonic vehicles with large volumes. The predominant visual feature of such configurations is a thin wing called a high-pressure capturing wing attached to the top of an upwarp airframe. When flying in the hypersonic regime, high-pressure airflow compressed by the upper surface of the vehicle acts on the high-pressure capturing wing and significantly augments lift on the vehicle with only a small increase in drag, producing a correspondingly high increase in its lift-to-drag ratio. A series of numerical validations were carried out on the basis of both inviscid and viscous computational models in which ideal cones with different cone angles and combined conewaverider bodies with different volumes were used as airframes. The results clearly demonstrate that a configuration using a high-pressure capturing wing has a significantly higher lift (with a correspondingly high value of lift-to-drag ratio) than one without a high-pressure capturing wing, especially for vehicles with large volumes. This paper contains a preliminary, results-based report of the conditions under which high-pressure capturing wing configurations were tested.= cruising speed W = gross weight, width α = angle of attack β = shock-wave angle γ = ratio of specific heats Δn = nondimensional height of the first layer near the wall η = ratio of average pressure on different surfaces θ = wedge angle, half-cone angle ξ = volumetric efficiency ρ = density Subscripts B = body H = high-pressure capturing wing HCWL = lower surface of the high-pressure capturing wing HCWU = upper surface of the high-pressure capturing wing

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Section: B Code Validation and Grid Convergence Testmentioning

confidence: 99%

High-Pressure Capturing Wing Configurations

Cui

Xiao

et al. 2017

AIAA Journal

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“…Improving the capacity of aircraft is essential work for their designers. According to the voyage equation, the lift-to-drag ratio of an aircraft is very important for enhancing the voyage in terms of keeping the oil costs low (Huang et al, 2012c), and this relates to the environment surrounding the aircraft. The choice of airfoil is of great importance in aircraft design; thus, it is very important to discover the characteristics of airfoils with different shapes.…”

Section: Introductionmentioning

confidence: 99%

A study of airfoil parameterization, modeling, and optimization based on the computational fluid dynamics method

Zhang

Huang

Wang

et al. 2016

J. Zhejiang Univ. Sci. A

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An excellent airfoil with a high lift-to-drag ratio may decrease oil consumption and enhance the voyage. Based on NACA 0012, an improved airfoil is explored in this paper. The class/shape function transformation has been proved to be a good method for airfoil parameterization, and in this paper it is modified to improve imitation accuracy. The computational fluid dynamics method is applied to obtain numerically the aerodynamic parameters of the parameterized airfoil, and the result is proved credible by comparison with available experimental data in the open literature. A polynomial-based response surface model and the uniform Latin hypercube sampling method are employed to decrease computational cost. Finally, the nonlinear programming by quadratic Lagrangian method is utilized to modify the multi-island genetic algorithm, which has an improved optimization effect than the method used on its own. The obtained result shows that the modified class/shape function transformation method produces a better imitation of an airfoil in the nose and tail regions than the original method, and that it will satisfy the tolerance zone of the model in a wind tunnel. The response surface model based on the uniform Latin hypercube sampling method gives an accurate prediction of the lift-to-drag ratio with changes in the design variables. The numerical result of the flow around the airfoil shows reasonable agreement with the experimental data graphically and quantitatively. Ultimately, an airfoil with better capacity than the original one is acquired using the multi-island genetic algorithm based nonlinear programming by quadratic Lagrangian optimization method. The pressure contours and lift-to-drag ratio along with the attack angle have been compared with those of the original airfoil, and the results demonstrate the strength of the optimized airfoil. The process for exploring an improved airfoil through parameterization to optimization is worth referencing in future work.

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“…1 (Pezzella, 2012). Such vehicles include hypervelocity projectiles, reentry vehicles (Ohtake, 1998;Huang et al, 2012b), and hypersonic aircraft (Huang et al, 2011). Fig.…”

Section: Introductionmentioning

confidence: 99%

A survey of drag and heat reduction in supersonic flows by a counterflowing jet and its combinations

Huang

2015

J. Zhejiang Univ. Sci. A

Self Cite

114

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Drag reduction and thermal protection is very important for hypersonic vehicles, and a counterflowing jet and its combinations is one of the most promising drag and heat release reduction strategies. In the current survey, research progress on the drag and heat release reduction induced by a counterflowing jet and its combinations is summarized. Three combinatorial configurations are considered, namely the combination of the counterflowing jet and a forward-facing cavity, the combination of the counterflowing jet and an aerospike, and the combination of the counterflowing jet and energy deposition. In conclusion, some recommendations are provided, especially for jet instability protection, for the tradeoff between drag and heat release reductions, and for the critical points for the operational and geometric parameters in the flow mode transition.

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Investigation on high angle of attack characteristics of hypersonic space vehicle

Cited by 48 publications

References 13 publications

High-Pressure Capturing Wing Configurations

High-Pressure Capturing Wing Configurations

A study of airfoil parameterization, modeling, and optimization based on the computational fluid dynamics method

A survey of drag and heat reduction in supersonic flows by a counterflowing jet and its combinations

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