Aerothermodynamics of the Waveriders Applying Artificially Blunted Leading Edge Concept

Pan, Jianguo; Yan, Chao; Geng, Yunfei; Wu, Jie

doi:10.2514/6.2009-748

Cited by 3 publications

(3 citation statements)

References 3 publications

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“…Although a detailed design and analysis of waverider blunt leading edges is beyond the scope of the present study, previous investigators have focused on this specific detailed design issue [8][9][10][11]. Vanmol and Anderson [8] performed a detailed study of waverider heat transfer, including the effects of leading-edge bluntness.…”

Section: A Sharp Leading-edge Assumptionmentioning

confidence: 99%

Star-Body Waveriders with Multiple Design Mach Numbers

Corda

2009

Journal of Spacecraft and Rockets

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A new type of star-body waverider is presented that has multiple design Mach numbers. A limitation of typical waverider configurations is that they have a single design Mach number, where the shock wave is attached to all of its leading edges. At this design Mach number, there is no flow spillage and the static pressure on the compression surfaces is maximized. The center wedge sections of the new star bodies have different flow deflection angles corresponding to different design Mach numbers, thereby generating lift and side force that can be used for increased range and maneuver capability. A baseline Mach 6, conventional star body, an equivalent volume cone, and three multiple-design-Mach-number star bodies are analyzed using three-dimensional, full Navier-Stokes computational fluid dynamics for Mach numbers of 4, 5, 6, 7, and 8 and an altitude of 100,000 ft. As expected, the conventional, single-design-Mach-number star body has higher skin-friction drag, lower wave drag, and lower total drag than the equivalent volume cone. Because the volumes of the multiple-design-Mach-number star bodies are greater than that of the cone, they have higher total drag than the cone, but the wave drag and drag coefficient are lower than the equivalent cone for some of the new configurations at higher Mach numbers. Before performing the analysis, it was assumed that the star body sectors at an on-design flow condition would have the greatest pressure levels. However, the computational fluid dynamics analysis showed that the star-body sectors with the maximum flow deflection (center wedge) angle produced the highest pressures, even at offdesign flow conditions, where three-dimensional effects and pressure loss due to detached shocks and flow spillage are present. The asymmetric, two-, and tripledesign-Mach-number star bodies produced lift that can be used for downrange and cross-range capability.

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Section: A Sharp Leading-edge Assumptionmentioning

confidence: 99%

Star-Body Waveriders with Multiple Design Mach Numbers

Corda

2009

Journal of Spacecraft and Rockets

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“…Other profiles of the leading edge of the waverider are also used in the bluntness of the waverider. In [21][22][23], the power curves and artificial blunt front were used to blunt the waverider. The design of the above blunt methods is complex and not convenient for design and manufacture.…”

Section: Introductionmentioning

confidence: 99%

Influence of Non-Uniform Bluntness on Aerodynamic Performance and Aerothermal Characteristics of Waverider

Wang

Xiao³

et al. 2023

Aerospace

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The waverider is widely used in hypersonic vehicles with its high aerodynamic performance, but due to the serious aerothermal environment, its sharp leading edge should be blunted. Circular blunt is one of the commonly used aerothermal characteristic protection methods. Circular blunt with larger diameter can reduce peak heat flux, but at the same time, it will lead to larger drag. The existing research shows that under the same blunt diameter in two-dimensions, the non-uniform blunt can reduce the peak heat flux by 20%, and the difference of drag is small. In this paper, the non-uniform blunt profile is applied to the three-dimensional waverider, and the influence of the non-uniform blunt profile on the aerothermal characteristic performance and aerodynamic performance of the waverider is studied, and the results are compared with those of circular blunt. The numerical simulation is used to compare and analyze the waverider under different angles of attack, flight altitudes, and Mach number. The results show that the peak heat flux of the waverider with non-uniform blunt reduces by about 17% compared with that with circular blunt under a small angle of attack range, Mach 2-10, and a flight altitude of 15–35 km. Meanwhile, when the blunt height/diameter is 20 mm, the aerodynamic performance difference between the two different blunt profiles does not exceed 3% within a 15 degrees angle of attack, Mach 2-10, and flight altitude of 15–35 km. The non-uniform blunt profile can be applied to the design of the three-dimensional waverider.

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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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Aerothermodynamics of the Waveriders Applying Artificially Blunted Leading Edge Concept

Cited by 3 publications

References 3 publications

Star-Body Waveriders with Multiple Design Mach Numbers

Star-Body Waveriders with Multiple Design Mach Numbers

Influence of Non-Uniform Bluntness on Aerodynamic Performance and Aerothermal Characteristics of Waverider

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

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