High-Pressure Capturing Wing Configurations

Cui, Kai; Li, Guangli; Xiao, Yong; Xu, Yanliang

doi:10.2514/1.j055395

Cited by 27 publications

(12 citation statements)

References 27 publications

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“…A quartic curve is selected as the projection curve of the leading-edge curve of the wings (curve 2-3, 7-17), and its equation is shown in Eq. (13). When the angle of the slope at the point 3 is zero degrees, and the coordinate values (z, y) at point 2 and point 3 are given in Eq.…”

Section: (7)mentioning

confidence: 99%

An airframe/inlet integrated full-waverider vehicle design using as upgraded aerodynamic method

et al. 2019

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With the aims of overcoming the limitations of the existing basic flow model derived from an axisymmetric generating body and extending the aerodynamic design method of the airframe/inlet integrated waverider vehicle, this study develops an upgraded basic flow model derived from an axisymmetric shock wave. It then upgrades the design method for airframe/inlet integration of an air-breathing hypersonic waverider vehicle, which is termed the ‘full-waverider vehicle’ in this study. In this paper, first, the design principle and method for the upgraded full-waverider vehicle derived from an axisymmetric basic shock wave are described in detail. Second, an upgraded basic flow model that accounts for both internal and external flows is derived from an axisymmetric basic shock wave by use of both the streamline tracing method and the method of characteristics (MOC). Third, the upgraded full-waverider vehicle is developed from the upgraded basic flow model by the streamline tracing method. Fourth, the design theories and methodologies of both the upgraded basic flow model and the upgraded full-waverider vehicle are validated by a numerical computation method. Finally, the aerodynamic performances and viscous effects of both the upgraded basic flow model and the upgraded full-waverider vehicle are analysed by numerical computation. The obtained results show that the upgraded basic flow model and aerodynamic design method are effective for the design of the airframe/inlet integration of an air-breathing hypersonic waverider vehicle.

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Section: (7)mentioning

confidence: 99%

An airframe/inlet integrated full-waverider vehicle design using as upgraded aerodynamic method

et al. 2019

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“…Ding Feng published several papers 8,[14][15][16][17][18] on the design method and fullscale waverider design, which provides an important reference for the design and application of waverider. Cui Kai et al [19][20][21] used a new method to derived the waverider configuration from the general conical flow field. In addition, the waverider configuration is applied to the design of high pressure capture wing, which can effectively improve the aerodynamic performance of the waverider aircraft.…”

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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“…Liu et al [13] investigated a wide-ranged multistage morphing waverider design method based on conical flowfield. To improve the performance of hypersonic vehicles with large volume, Cui et al [14] proposed a family of aircraft with high-pressure capturing wing (HCW) configurations, the numerical results demonstrated that HCW could gain considerable lift-to-drag ratio and higher volumetric efficiency. In addition, Rodi [15] exploited vortex lift to generate a waverider by the osculating-cone waverider method and geometrical relationships.…”

Section: Introductionmentioning

confidence: 99%

Waverider Configuration Design With Variable Shock Angle

et al. 2019

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A novel waverider design methodology is proposed with a variable shock angle based on the osculating cones' theory. The expected shape with special requirements can be generated by arranging the distribution of shock angle using the new method. Contrast investigation is conducted on three waveriders, which are designed with constant, decreasing and increasing shock angle distribution starting from symmetry plane at the average shock angle of 12 •. The feasibility of the proposed approach is validated by the computational fluid dynamics (CFD) simulation. The results show that the distribution of shock angle has a significant influence on the lift-to-drag ratio and volumetric efficiency. Waverider with decreasing shock angle owns the greater volume and volumetric efficiency but with weak aerodynamic performance. The waverider with increasing shock angle has a higher lift-to-drag ratio and enhanced the static stability but with lower volumetric efficiency. The performance of waveriders with variable shock angle under off-design and blunted conditions is also investigated, which reveals a great overall aerodynamic performance and good robustness. INDEX TERMS Hypersonic waverider, variable shock angle, lift-to-drag ratio, off-design condition, bluntness.

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High-Pressure Capturing Wing Configurations

Cited by 27 publications

References 27 publications

An airframe/inlet integrated full-waverider vehicle design using as upgraded aerodynamic method

An airframe/inlet integrated full-waverider vehicle design using as upgraded aerodynamic method

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

Waverider Configuration Design With Variable Shock Angle

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