Avoiding Choked Flow and Flow Hysteresis of Busemann Biplane by Stagger Approach

Ma, Boping; Wang, Gang; Wu, Jie; Ye, Zhengyin

doi:10.2514/1.c035664

Cited by 8 publications

(3 citation statements)

References 21 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%

“…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

View full text Add to dashboard Cite

show abstract

“…Since then, supersonic biplane concepts have mostly been investigated by 2-D numerical flow simulation, and valuable aerodynamic results have been obtained. [6][7][8][9] In recent years, the complex 3-D flow field caused by in-terference between the shock wave generated from the fuselage and the biplane main wing has been investigated numerically and experimentally to obtain more detailed aerodynamic data for aircraft design. [10][11][12][13] Moreover, a low-boom fuselage designed with reference to the concepts of a twin body and a Sears-Haack body has been investigated by 3-D numerical simulation.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Characteristics of Busemann Biplane by Wake Measurements in Low-Speed Wind Tunnel

Kashitani

Duong

Kusunose

et al. 2021

Trans. Japan Soc. Aero. S Sci.

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In this study, the basic aerodynamic characteristics of a Busemann biplane model in a low-speed wind tunnel were clarified by the wake survey technique. A low-speed wind tunnel of the blowdown type was used, and it had an exit nozzle size is in 1.5 m © 1.5 m. A wake measurement system and six-component balance system were installed in the test section. A five-hole probe was used in the wake measurement system to measure the velocity distribution. The Busemann biplane model was designed to cruise at Mach 1.7. The total length of the model was 742 mm, and the width was 556 mm. The shape of the fuselage was 76 mm square on a side, and the nose had a double-conical shape. The flow velocity was 20 m/s, and the Reynolds number derived from the mean chord length was 1.4 © 10 5 . The results of the study are summarized as follows. Based on the visualization of the wake flow, vortices were generated from the tips of the upper and lower wing elements of the biplane at an attack angle of ¡ = 0°, but the vortices had an opposing rotation direction. Analysis of the wake data showed that locally induced drag was not generated at the wing tip. At ¡ = 6°and 8°, the profile drag increased, probably due to the influence of the flow separation from the upper surface of the upper wing element. However, the total lift coefficient increased with an increasing angle of attack, even at ¡ > 8°. Therefore, it can be concluded that the biplane lift is mainly generated by the lower wing elements.

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Optimization of thin electric propeller using physics-based surrogate model with space mapping

Mian

Wang

Zhou

et al. 2021

Aerospace Science and Technology

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Avoiding Choked Flow and Flow Hysteresis of Busemann Biplane by Stagger Approach

Cited by 8 publications

References 21 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

Aerodynamic Characteristics of Busemann Biplane by Wake Measurements in Low-Speed Wind Tunnel

Optimization of thin electric propeller using physics-based surrogate model with space mapping

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