Design of a new supersonic biplane

Zhai, Jing; Zhang, Chen-An; Wang, Famin; Zhang, Weiwei

doi:10.1016/j.actaastro.2020.05.010

Cited by 4 publications

(3 citation statements)

References 33 publications

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“…A new design for the supersonic biplane shown in Figure 31 was developed in 2020 [199], which improves aerodynamic performance in both design and off-design conditions. It consists of an isosceles triangle airfoil and a flat plate, and has the aerodynamic advantages of lower drag, higher lift-to-drag ratio, and a weaker flow-choking phenomenon than the Busemann biplane.…”

Section: Supersonic Biplanementioning

confidence: 99%

Review of Sonic Boom Prediction and Reduction Methods for Next Generation of Supersonic Aircraft

Bonavolontà,

Lawson,

Riaz

2023

Aerospace

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The reduction of sonic boom levels is the main challenge but also the key factor to start a new era of supersonic commercial flights. Since 1970, a FAA regulation has banned supersonic flights overland for unacceptable sonic booms at the ground, and many research studies have been carried out from that date to understand sonic boom generation, propagation and effects, both on the environment and communities. Minimization techniques have also been developed with the attempt to reduce sonic boom annoyance to acceptable levels. In the last 20 years, the advances in both knowledge and technologies, and companies and institutions’ significant investments have again raised the interest in the development of new methods and tools for the design of low boom supersonic aircraft. The exploration of unconventional configurations and exotic solutions and systems seems to be needed to effectively reduce sonic boom and allow supersonic flight everywhere. This review provides a description of all aspects of the sonic boom phenomenon related to the design of the next generation of supersonic aircraft. In particular, a critical review of the prediction and minimization methods found in the literature, aimed at identifying their strengths, limitations and gaps, is made, along with a complete overview of disruptive unconventional aircraft configurations and exotic active/passive solutions to boom level reduction. The aim of the work is to give a clear statement of state-of-the-art sonic boom prediction methods and possible reduction solutions to be explored for the design of next low-boom supersonic aircraft.

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Section: Supersonic Biplanementioning

confidence: 99%

Review of Sonic Boom Prediction and Reduction Methods for Next Generation of Supersonic Aircraft

Bonavolontà,

Lawson,

Riaz

2023

Aerospace

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“…A pair of isosceles triangular wings make up a traditional Bussemann wing. In the presence of certain supersonic airflow, the interference effect between the targeted Bussemann-style supersonic biplane wing designs can be used to effectively lessen the sonic boom and wave drag [1]. In many instances, shock oscillations between the wings are produced when air-flow stratification occurs close to the wing lateral boundaries, which is influenced by the resilient properties of the wing framework.…”

Section: Introductionmentioning

confidence: 99%

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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“…Under design conditions, the new supersonic biplane has the same wavecancellation effect as the Busemann biplane. It also has a weaker flow choking issue in off-design conditions because of a higher ratio of the throat area to the inlet area [17][18][19].…”

Section: Introductionmentioning

confidence: 99%

Numerical analysis of stagger Supersonic biplane at off-design condition with trailing edge flap

Patidar¹,

Joshi²

2023

FME Transactions

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Supersonic biplanes can achieve low-boom and low-drag supersonic flights. In the present study, aerodynamic analysis of a two-dimensional stagger Bussmann biplane (staggered upper element by 0.5c) at zero degrees angle of attack with trailing edge flap was investigated with the help of computational fluid dynamics (CFD) tools. Due to the wave cancellation effect, the Busemann biplane delivers a positive drag reduction at design supersonic Mach values. However, when operating outside of its intended parameters, it performs worse, and the wave cancellation effect has no beneficial effects on reducing drag. Another issue with the Busemann biplane is flow chocking, which produces a potent bow shock wave in front of the aircraft. This paper attempts to address low aerodynamics efficiency problems during take-off through numerical simulation of a staggered Busemann biplane with trailing edge flaps at zero degrees angle of attack. It was confirmed that the staggered biplane airfoil with flap has better aerodynamic performance during take-off at lower subsonic free stream Mach numbers. In 2D wings, the effect of flow chocking and hysteresis as starting problems, which arise when the biplanes accelerate from low Mach numbers, is reduced by using the suitable dimension and angle of rotation of the flap, and the flap is effective in settling these issues.

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Design of a new supersonic biplane

Cited by 4 publications

References 33 publications

Review of Sonic Boom Prediction and Reduction Methods for Next Generation of Supersonic Aircraft

Review of Sonic Boom Prediction and Reduction Methods for Next Generation of Supersonic Aircraft

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

Numerical analysis of stagger Supersonic biplane at off-design condition with trailing edge flap

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