Bluntness Effects on Lift-to-Drag Ratio of Leading Edges for Hypersonic Waverider Configurations

Santos, Wilson F. N.

doi:10.2514/6.2011-2321

Cited by 3 publications

(3 citation statements)

References 12 publications

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“…Therefore, the aerodynamic heating problem is more prominent in the hypersonic aircraft design, and the thermal protection of aircraft is one of the important links in the design. The results show that the heat flux at the stagnation point is inversely proportional to the radius of curvature, and the larger the radius of curvature is, the lower the heat flux is [3] . Therefore, the design of the leading edge of a hypersonic vehicle requires a trade-off between two aspects: on the one hand, the leading edge should be sharp enough to obtain acceptable aerodynamic performance; on the other hand, the leading edge should be blunt enough to reduce aerodynamic heating in the stagnation region.…”

Section: Introductionmentioning

confidence: 96%

Study on heat reduction and lift-to-drag ratio increase of two-dimensional wedge-shaped waverider blunt leading edges and high pressure capture wing^[1] combined configuration

Guo

Fang

2022

J. Phys.: Conf. Ser.

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In this paper, the aerodynamic and aerothermal performance of the simplified two-dimensional wedge-shaped waverider bluntness leading edge and high pressure capture wing(HCW) combined configuration in a hypersonic continuous flow basin is numerically simulated by the Computational Fluid Dynamics (CFD) method, the flow field structure of the model is analyzed, and the law of anti-thermal rise is revealed. The main contents of the study include the surface heat flux and lift-drag ratio characteristics of the bluntness leading edge under different bluntness radii, the lift-to-drag ratio, and surface heat flux characteristics of the composite configuration of the bluntness leading edge and the high pressure capture wing under different bluntness radius. Within the scope of the study: 1. The larger the bluntness radius is, the more effective it is to reduce the heat flux of the head. When the bluntness radius is 2mm, the decrease is about 82.5%;2. The larger the bluntness radius is, the more serious the lift-drag ratio decreases. When the bluntness radius is 2mm, the lift-drag ratio decreases by about 72.4%;3. The combined configuration of the bluntness leading edge and the high pressure capture wing can effectively reduce the head heat flux under the premise of ensuring a certain lift-drag ratio. The optimal bluntness radius is 1mm, the head heat flux decreases by about 76% and the lift-drag ratio only decreases by 24%.

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Section: Introductionmentioning

confidence: 96%

Study on heat reduction and lift-to-drag ratio increase of two-dimensional wedge-shaped waverider blunt leading edges and high pressure capture wing^[1] combined configuration

Guo

Fang

2022

J. Phys.: Conf. Ser.

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show abstract

“…Therefore, the aerodynamic heating problem is more prominent in the hypersonic aircraft design, and the thermal protection of aircraft is one of the important links in the design. The results show that the heat flux at the stagnation point is inversely proportional to the radius of curvature, and the larger the radius of curvature is, the lower the heat flux is [2] . Therefore, the design of the leading edge of a hypersonic vehicle requires a trade-off between two aspects: on the one hand, the leading edge should be sharp enough to obtain acceptable aerodynamic performance; on the other hand, the leading edge should be blunt enough to reduce aerodynamic heating in the stagnation region.…”

Section: Introductionmentioning

confidence: 96%

Study on aerodynamic force and aerothermal effect of two-dimensional wedge wave rider with different passivation shape of the head

Guo

Fang

2022

J. Phys.: Conf. Ser.

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With the rapid development of space technology, hypersonic vehicles flying at altitudes of 20-100 km near space are showing more and more important application value, and how to solve the serious aerodynamic heating problem caused by hypersonic vehicles in the process of flight is the focus of current research. In this paper, the simplified two-dimensional wedge-shaped waveride is treated with the passivation leading edge by the Computational Fluid Dynamics (CFD) method, and the aerodynamic and aerothermal properties of the hypersonic continuous flow basin are numerically simulated. The flow field structure of the model is analyzed, and the law of heat-resistant rise is revealed. The research contents mainly include the characteristics of body head heat flux and body lift-drag ratio under different passivation shapes. Within the research scope: 1. The larger the passivation radius, the more effective it is to reduce the head heat flux. When the passivation radius is 2 mm, the reduction is about 82.5%. 2. The larger the passivation radius, the more serious the lift-drag ratio reduction. When the passivation radius is 2mm, the maximum reduction is about 72.4%; 3. The four passivation leading edge modes have the best thermal protection effect when the passivation radius R is the same, and the lift-drag ratio of the Bezier curve passivation leading edge mode is the largest.

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“…The influence of bluntness on the aerodynamic performance of waverider was studied by experiment in literature. 31,32 In addition, the influence of power curve bluntness 33 and artificial blunt leading edge 34 on the aerodynamic performance of the blunt waverider is also studied; the aerodynamic performance of the blunt waverider in the rarefied gas 35 is analyzed.…”

Section: Introductionmentioning

confidence: 99%

Numerical study on aerodynamic performance of waverider with a new bluntness method

Xiao

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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Abastrct The waverider is deemed the most promising configuration for hypersonic vehicle with its high lift-to-drag ratio at design conditions. However, considering the serious aero-heating protection, the sharp leading edge must be blunted. The existing traditional bluntness methods including the following two types: “reducing material method” and “adding material method”. Compared to the initial waverider, the volume will be smaller or larger using the traditional methods. With the fixed blunted radius, the volume and aerodynamic performance is determined. In this paper, a new bluntness method which is named “mixing material method” is developed. In this new method, a new parameter is introduced based on the traditional two bluntness methods. Under fixed blunted radius, the volume and aerodynamic performance can be changed within a wide range by adjusting the parameter. When the parameter is 0 and 1, the novel blunted method degenerated into the “reducing material method” and “adding material method” respectively. The influence of new parameter on the aerodynamic characteristics and volume are studied by numerical simulation. Results show that the volume, lift and lift-to-drag ratio increases with the increase of the parameter under the fixed blunt radius, but simultaneously, the drag will also increase. Therefore, considering the different requirements of the air-breathing hypersonic aircrafts for the balance of thrust and drag, lift and weight, a suitable bluntness parameter can be selected to achieve a balance. This research can provide reference for hypersonic waverider vehicle design.

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Bluntness Effects on Lift-to-Drag Ratio of Leading Edges for Hypersonic Waverider Configurations

Cited by 3 publications

References 12 publications

Study on heat reduction and lift-to-drag ratio increase of two-dimensional wedge-shaped waverider blunt leading edges and high pressure capture wing^[1] combined configuration

Study on heat reduction and lift-to-drag ratio increase of two-dimensional wedge-shaped waverider blunt leading edges and high pressure capture wing^[1] combined configuration

Study on aerodynamic force and aerothermal effect of two-dimensional wedge wave rider with different passivation shape of the head

Numerical study on aerodynamic performance of waverider with a new bluntness method

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Bluntness Effects on Lift-to-Drag Ratio of Leading Edges for Hypersonic Waverider Configurations

Cited by 3 publications

References 12 publications

Study on heat reduction and lift-to-drag ratio increase of two-dimensional wedge-shaped waverider blunt leading edges and high pressure capture wing[1] combined configuration

Study on heat reduction and lift-to-drag ratio increase of two-dimensional wedge-shaped waverider blunt leading edges and high pressure capture wing[1] combined configuration

Study on aerodynamic force and aerothermal effect of two-dimensional wedge wave rider with different passivation shape of the head

Numerical study on aerodynamic performance of waverider with a new bluntness method

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Study on heat reduction and lift-to-drag ratio increase of two-dimensional wedge-shaped waverider blunt leading edges and high pressure capture wing^[1] combined configuration

Study on heat reduction and lift-to-drag ratio increase of two-dimensional wedge-shaped waverider blunt leading edges and high pressure capture wing^[1] combined configuration