Numerical study on the influence of wall temperature gradient on aerodynamic characteristics of low aspect ratio flying wing configuration

Peng, Lin; Liu, Xueqiang; Xiong, Neng; Wang, Xiaobing; Ma, Shuai; Liu, Guangyuan; Tao, Yang

doi:10.1038/s41598-021-94261-x

Cited by 3 publications

(3 citation statements)

References 11 publications

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“…Both effects contributed to an increase in pressure drag with rising heat flux qA . This behavior is aligned with effects reported in the literature [20,40,44,45]. For cruise conditions, the drag coefficient C d is reduced for small temperature differences between the airfoil surface and freestream flow for small and high α.…”

Section: Uniformly Heated Two-dimensional Airfoilsupporting

confidence: 90%

“…In the present study, the flow is characterized as fully turbulent and, consequently, the effects of heating on the transition from laminar to turbulent flow were not studied. Studies on the impact of heating on BL transition can be found in the literature (e.g., [37,39,44]). The existence of a PI is also directly related to the pressure gradient in the flow direction.…”

Section: Consequences On Aerodynamicsmentioning

confidence: 99%

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Aerodynamic Effects of a Wing Surface Heat Exchanger

et al. 2023

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One challenge for the design and analysis of hybrid electric aircraft configurations is an increased demand in the rejection of excess waste heat. A wing surface heat exchanger concept, which is explored as part of the IMOTHEP project, foresees transferring heat from the propulsive electrical components to the wing surface of the aircraft. Here, heat is mainly dissipated and transported by forced convection. The present study focuses on the analysis of the impact of heat rejection via the wing surface on the wing’s heat transfer and aerodynamic efficiency characteristics. For this purpose, RANS CFD studies of 2D airfoils and a 3D wing propeller geometry of a regional turboprop configuration in representative flight conditions (take off, cruise, and taxi in) are carried out. For each condition, the influence of defining parameters, such as altitude, freestream velocity, angle of attack, surface temperature, and propeller thrust is explored. It is shown that, when increasing the wing surface temperature compared against the freestream temperature, the aerodynamic efficiency of the wing deteriorates for all flight conditions. In reference cruise conditions for example, the lift-to-drag ratio decreases by 4%, while the average heat transfer coefficient is reduced by almost 20% when increasing the surface temperature by 300 K. Furthermore, the propeller slipstream enhances the wing’s heat transfer capacity significantly.

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Section: Uniformly Heated Two-dimensional Airfoilsupporting

confidence: 90%

Section: Consequences On Aerodynamicsmentioning

confidence: 99%

Aerodynamic Effects of a Wing Surface Heat Exchanger

et al. 2023

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“…Re-Entry Capsules (REC) have been instrumental in the history of human spaceflight, ensuring the safe return of astronauts, scientific experiments and samples from space and delivering payloads to Earth. REC pass through hypersonic flow during their return journey, characterized by speeds exceeding five times the speed of sound (Mach > 5), which pose unique challenges in both experimental and modelling studies due to its high temperatures, velocities, and exceptional conditions [1]. Understanding hypersonic flow involves grasping physical flow phenomena, such as shock waves, flow separation, and boundary layer transition [2].…”

Section: Introductionmentioning

confidence: 99%

Parametric Optimisation of Hypersonic Re-entry Capsules with Air-Duct Systems

Al Qubeissi,

Shaban,

Almohammadi

et al. 2023

Preprint

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This study focuses on the aerodynamic optimization of the re-entry capsule (REC) Orion Crew Exploration Vehicle (CEV) module, evaluating its performance using computational fluid dynamics (CFD). Three different models, namely Baseline, 2-Duct, and 4-Duct, are investigated under a wide range of flow speeds, from supersonic (Ma=1.6) to hypersonic (Ma=6) regimes. Thermofluids aspects, drag coefficient, surface heat flux, and the effectiveness of the modified geometry are assessed using aerodynamic and temperature-based models. The results show that the introduction of ducts in the 2-Duct and 4-Duct models leads to an average decrease in the drag coefficient of approximately 2.1% and 2.9%, respectively, compared to the baseline model, across all Mach numbers. The maximum reduction in drag coefficient is 3.55%, observed at Ma=1.4 using the 4-Duct capsule. However, it is found that the addition of extra ducts to the model increases the maximum heat transfer rate. Specifically, the heat flux is increased by up to 69% for the 4-Duct model at Ma=6, compared to the baseline model. On average, the heat flux is increased by approximately 28.6% for all conditions. The findings indicate that the introduction of ducts in the REC model improves its aerothermodynamic performance by reducing drag but also increases the heat transfer rate on the surface.

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Investigation on the Reynolds Number Effect of a Flying Wing Model with Large Sweep Angle and Small Aspect Ratio

Peng

et al. 2022

Aerospace

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The effect of the Reynolds number on the flying wing common research model with a large sweep angle and small aspect ratio is studied by numerical simulation. The helicity cross-flow transition correction of the Langtry–Menter model is established in view of the deficient prediction accuracies of existing transition prediction models in simulating cross-flow transition, and the helicity parameters are calibrated to improve the prediction accuracy of the numerical method. The transition prediction method is verified by the test results of the standard model transition of the DLR-F5 wing and small-aspect-ratio flying wing. At the same time, the numerical method is effectively verified by comparing it to the aerodynamic/torque results of the standard model of the small-aspect-ratio flying wing. On this basis, the variation laws with the Reynolds number are analyzed for the aerodynamic and flow field characteristics of the flying wing common research model with a large sweep angle and small aspect ratio. The numerical simulation is mainly carried out in the high subsonic speed range (M = 0.9), and the simulated Reynolds number range is from 2 × 106 to 80 × 106, which includes the test Reynolds number and flight Reynolds number. The influence of turbulence on the surface flow pattern and drag characteristics of the small-aspect-ratio standard model is analyzed. Calculation results show that when the turbulence is greater than 0.4%, it has a considerable influence on the surface laminar flow range and total drag coefficient. The results reveal that the Reynolds number mainly affects the magnitude of friction in the cruise state (small angle of attack). The problem of the Reynolds number in the self-aligning region of the flying wing standard model with a small aspect ratio is further studied, and the Reynolds number is found to be greater than 10 × 106. The drag and lift coefficients after the approach are close to the Reynolds number in the self-aligning region of the flying wing standard model with a small aspect ratio.

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Numerical study on the influence of wall temperature gradient on aerodynamic characteristics of low aspect ratio flying wing configuration

Cited by 3 publications

References 11 publications

Aerodynamic Effects of a Wing Surface Heat Exchanger

Aerodynamic Effects of a Wing Surface Heat Exchanger

Parametric Optimisation of Hypersonic Re-entry Capsules with Air-Duct Systems

Investigation on the Reynolds Number Effect of a Flying Wing Model with Large Sweep Angle and Small Aspect Ratio

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