Influence of surface pressure distribution of basic flow field on shape and performance of waverider

Ding, Feng; Shen, Chibing; Liu, Jun; Huang, Wei

doi:10.1016/j.actaastro.2014.11.038

Cited by 36 publications

(14 citation statements)

References 25 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…18. This figure shows that at both the design and the off-design flight Mach numbers, the viscous effects on the drag coefficients and lift-to-drag ratios decrease with increasing angle of attack, owing to the fact that the ratio of the skin friction drag to the total drag decreases with the increase of angle of attack [7]. Fig.…”

Section: Case Verificationmentioning

confidence: 88%

Novel approach for design of a waverider vehicle generated from axisymmetric supersonic flows past a pointed von Karman ogive

Ding

Liu

Shen

et al. 2015

Aerospace Science and Technology

Self Cite

View full text Add to dashboard Cite

Section: Case Verificationmentioning

confidence: 88%

Novel approach for design of a waverider vehicle generated from axisymmetric supersonic flows past a pointed von Karman ogive

Ding

Liu

Shen

et al. 2015

Aerospace Science and Technology

Self Cite

View full text Add to dashboard Cite

“…. (9) Table 2 lists the specific parameters for the basic flow model. As shown in Table 2, θ DC,2 is the distribution of the flow angles θ just downstream of the lip shock wave DC; M CG and δ CG are the distributions of the Mach number and the angle of the slope along the wall CG, respectively, and the condition M CG (x) = M C means that the Mach numbers along the wall CG are equal to the Mach number at the point C; x CF is the distance from the inlet exit plane to point C along the x axis direction, and the length 1.3 m chosen in this case is about 8 times of the inlet height at the inlet exit plane.…”

Section: (7)mentioning

confidence: 99%

“…The waverider first proposed by Nonweiler (7) in 1959 is any hypersonic lifting body with an attached shock wave along its leading edge (8)(9)(10)(11)(12)(13)(14) . Since then, because of the excellent aerodynamic configuration of the waverider, it has become one of the most ideal aerodynamic configurations for hypersonic vehicles.…”

Section: Introductionmentioning

confidence: 99%

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

et al. 2019

View full text Add to dashboard Cite

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.

show abstract

“…Although the numerical method in this study failed to reflect the influence of laminar-to-turbulent transition in Sharma et al (2018), and Chaudhuri et al (2011) on aerodynamic characteristics, the main flow field wave system structure is captured. In the literature (Ding et al, 2015), a similar method to solve the Euler equation was adopted to verify the applicability of the design configuration in the study of wave-rider theory.…”

Section: Flow Field Analysismentioning

confidence: 99%

Assessment of Numerical Method by Experimental Data for Integrated Hypersonic Vehicles

Wen

Liu

et al. 2019

JAFM

View full text Add to dashboard Cite

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.

show abstract

Influence of surface pressure distribution of basic flow field on shape and performance of waverider

Cited by 36 publications

References 25 publications

Novel approach for design of a waverider vehicle generated from axisymmetric supersonic flows past a pointed von Karman ogive

Novel approach for design of a waverider vehicle generated from axisymmetric supersonic flows past a pointed von Karman ogive

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

Assessment of Numerical Method by Experimental Data for Integrated Hypersonic Vehicles

Contact Info

Product

Resources

About