Numerical analysis on flutter of Busemann-type supersonic biplane airfoil

Zhou, Hao; Wang, Gang; Liu, Zhikan

doi:10.1016/j.jfluidstructs.2019.102788

Cited by 14 publications

(5 citation statements)

References 36 publications

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“…Substitute Equation (8) into Equation (7), the small disturbance along the stream can now be expressed in Equation ( 9), where M∞ is just 1.95.…”

Section: Small Disturbance Methods Applied From Full Potential Equationmentioning

confidence: 99%

“…For a wing operating at supersonic circumstances, the resultant wave drag is proportional to the thickness of the wing [6]. In addition, compared with the solid wing isolated in the supersonic airflow, considering the impact of the shock oscillation between the two wings caused by the vibration of the wing on the wing stability, the wing stability of the supersonic biplane system been weakened [7]. Therefore, the maximum and minimum ratios of a biplane wing are limited by both wave resistance and stability, and may now be bounded by Equations ( 1) and (2) [5,8]:…”

Section: Airfoil Geometrymentioning

confidence: 99%

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Density and Small Disturbance Equation-Based Simulation of Designed Bipalne Airfoil Under Supersonic Flow

Liu¹

2023

HSET

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For inviscid airflows, the small disturbance equation (SDE), as a condensed form of the full potential equation, is an effective approach for characterising the behaviour of this type of airflow in the presence of thin obstacles in its path. Density-based solutions (DBS) are frequently used by ANSYS to model the airflow behavior under the same environment. Through the impact of shock interference between the target wings, special Bussemann-type supersonic biplane designs can be effective in restricting sonic booms and wave drags in particular supersonic conditions. The modeling investigations of the shock oscillations produced between the wings are quite rare, nevertheless. Therefore, in order to replicate the behavior of the airflow over the target wing in supersonic settings and to compare the results more closely to reality, the Small Disturbance Equation (SDE) and the Density Based Solution (DBS) will be employed as efficient simulation tools in this study. The SDE results are vulnerable to inaccuracies because of the constraints of the simulation settings, whereas the DBS results are more accurate when compared to the exact simulation results. Overall, the DBS simulation results and the legit results are consistent, indicating that the inviscid airflow hypothesis is a feasible option for modelling the effectiveness of shock oscillations between wings. The SDE approach, which is implemented in Python and is a condensed version of the en-tire potential equation, offers a lot of space for development as it only does simulations in terms of velocity in this article and ignores the pressure and density elements.

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“…Substitute Equation (8) into Equation (7), the small disturbance along the stream can now be expressed in Equation ( 9), where M∞ is just 1.95.…”

Section: Small Disturbance Methods Applied From Full Potential Equationmentioning

confidence: 99%

Section: Airfoil Geometrymentioning

confidence: 99%

Density and Small Disturbance Equation-Based Simulation of Designed Bipalne Airfoil Under Supersonic Flow

Liu¹

2023

HSET

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“…Mean angles of attack [20], Reynolds number [21], flexible extent [22,23] and flapping modes [24][25][26][27] have been extensively studied to reveal the interference effects. Zhou et al [28] discussed the effects of the position of the mass center on the system's aeroelastic stability.…”

Section: Nomenclature αmentioning

confidence: 99%

Effects of Pivot Point and Spacing on the Aerodynamic Characteristics of Tilting Biplane Airfoils

et al. 2022

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“…The fluid-structure dynamic system of the supersonic biplane is investigated using the two-way computational fluid dynamics/computational structural dynamics (CFD/CSD) coupling method in conjunction with unsteady Navier-Stokes equations. [8] SetoguchiIn et.al (2020) investigated the phenomenon of the separation vortex from the leading edge, in the low-speed and high angle of attack regime, the aerodynamic characteristics of a supersonic business jet with a forward-swept wing were numerically evaluated.…”

Section: Literature Reviewmentioning

confidence: 99%

Theoretical and Computational Investigation on Swept Back Wing using CFD Method

Bindal¹,

Mishra²

2022

jame

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The principles of flight deals with the motion of air and forces acting on an aircraft. The theoretical aspects of aircraft deals with four different forces. The main aim of the study was to analyse the Swept Back Wing for Supersonic and Hypersonic Mach Regimes at various angles of attack. The geometry and analysis were done using Ansys-Fluent. Calculations were done for constant air velocity altering only the angle of attack. The findings present up the contours of pressure and velocity along with evaluation of lift, drag and its coefficients

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Numerical analysis on flutter of Busemann-type supersonic biplane airfoil

Cited by 14 publications

References 36 publications

Density and Small Disturbance Equation-Based Simulation of Designed Bipalne Airfoil Under Supersonic Flow

Density and Small Disturbance Equation-Based Simulation of Designed Bipalne Airfoil Under Supersonic Flow

Effects of Pivot Point and Spacing on the Aerodynamic Characteristics of Tilting Biplane Airfoils

Theoretical and Computational Investigation on Swept Back Wing using CFD Method

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