Far-field drag decomposition using hybrid formulas and vorticity based area sensors

Qiao, Li; Xu, He; Sun, Yihan; Bai, JQ; Li, L

doi:10.1177/0954410020973904

Cited by 4 publications

(4 citation statements)

References 35 publications

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“…In practice, a threshold value of 𝜁 ≃ 0.95 has been found to provide adequate treatment for the inclusion of the numerical shock domain, in agreement with previous observations by [22,45], whereas detailed discussions on the identification of boundary layer and shock wave regions are given in Reference [46]. 𝑑𝑠 term, indicating conceptually that pressure drag is generated at airframe regions with large viscous displacement under adverse pressure gradients (𝑑𝑉 𝑒 /𝑑𝑠 < 0) [43].…”

Section: Shock Wavessupporting

confidence: 84%

Energy-Based Aerodynamic Loss and Recovery Characteristics of Adiabatic and Heated Fuselages

Lamprakis

Sanders

Laskaridis

2023

Journal of Aircraft

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An energy-based aerodynamic analysis of the mechanical loss generation and potential energy/exergy recovery mechanisms is carried out for adiabatic and heated 2D axisymmetric flows over fuselage-shaped axisymmetric bodies. A generality of these mechanisms is obtained from dimensional analysis by appropriately scaling the freestream Reynolds and Mach numbers, while varying a reference fuselage’s fineness ratio. Thermo-aerodynamic implications and synergies of boundary-layer heating on the loss distribution, energy, and heat exergy recovery potentials are further considered for varying wall temperature ratios. The result is a clear identification of partial dynamic similarity and heat transfer effects on flow mechanisms such as shear layers, separation bubbles, and shockwaves of axisymmetric flows, and subsequent implications on loss distribution and energy recovery characteristics relating to boundary-layer ingestion. The analysis indicates that dissipating heat from aircraft surfaces aids, circumstantially, to drag reduction of unpowered fuselage bodies and increases, relative to the adiabatic, the recoverable energy fraction available for the boundary-layer ingestion propulsor, by strategically manipulating the loss distribution, while removing excess heat from the aircraft’s subsystem (batteries, fuel cells). Finally, an approach to assess the feasibility of exergetic heat recuperation as a possible means of useful work extraction and improved aerodynamic performance is explicitly introduced and discussed in the paper.

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Section: Shock Wavessupporting

confidence: 84%

Energy-Based Aerodynamic Loss and Recovery Characteristics of Adiabatic and Heated Fuselages

Lamprakis

Sanders

Laskaridis

2023

Journal of Aircraft

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“…The results are shown in Table 4. For the L0 grid, the viscous drag of "DP" [47] is larger than that of ONERA by 0.2 counts, which indicates a good match. The wave drag and induced drag also match well between the "DP" and ONERA.…”

Section: Test Casementioning

confidence: 88%

“…and we call it "Gariepy". According to Qiao et al [47], the first formula Equation ( 46) has the best stability, but the drag prediction accuracy is slightly poor, and the definition of induced drag is lacking. The other two formulas (Equations ( 47) and ( 48)) lack definitions in specific areas.…”

Section: Far-field Drag Decomposition Methodsmentioning

confidence: 99%

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Aerodynamic Robust Design Research Using Adjoint-Based Optimization under Operating Uncertainties

Ma,

Du,

Yang

et al. 2023

Aerospace

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Robust optimization design (ROD) is playing an increasingly significant role in aerodynamic shape optimization and aircraft design. However, an efficient ROD framework that couples uncertainty quantification (UQ) and a powerful optimization algorithm for three-dimensional configurations is lacking. In addition, it is very important to reveal the maintenance mechanism of aerodynamic robustness from the design viewpoint. This paper first combines gradient-based optimization using the discrete adjoint-based approach with the polynomial chaos expansion (PCE) method to establish the ROD framework. A flying-wing configuration is optimized using deterministic optimization and ROD methods, respectively. The uncertainty parameters are Mach and the angle of attack. The ROD framework with the mean as an objective achieves better robustness with a lower mean (6.7% reduction) and standard derivation (Std, 18.92% reduction) compared to deterministic results. Moreover, we only sacrifice a minor amount of the aerodynamic performance (an increment of 0.64 counts in the drag coefficient). In comparison, the ROD with Std as an objective obtains a very different result, achieving the lowest Std and largest mean The far-field drag decomposition method is applied to compute the statistical moment variation of drag components and reveal how the ROD framework adjusts the drag component to realize better aerodynamic robustness. The ROD with the mean as the objective decreases the statistical moment of each drag component to improve aerodynamic robustness. In contrast, the ROD with Std as an objective reduces Std significantly by maintaining the inverse correlation relationship between the induced drag and viscous drag with an uncertainty parameter, respectively. The established ROD framework can be applied to future engineering applications that consider uncertainties. The unveiled mechanism for maintaining aerodynamic robustness will help designers understand ROD results more deeply, enabling them to reasonably construct ROD optimization problems.

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Sustainable Technology on Aircraft Design: A Review

Dhara

Lal

2021

IOP Conf. Ser.: Earth Environ. Sci.

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Next-generation air transportation is a key to influence the environment, safety, and the economy. Several programs strive to create emerging innovation towards sustainability, system integrity, and alternative fuels to guarantee a reduction of its environmental effect as greenhouse gas. Nowadays, the aerospace industry is looking forward to aviation sustainable developments across the globe. Few initiatives through a novel configuration of aircraft is established like Blended Wing Body, Flying V aircraft, Box wing Aircraft, and Double bubble Aircraft to enhance the cargo and passenger volume occupancy and cut-off the fuel burn percent. With the use of disruptive technologies, researchers are progressing the revolutionary airframe for transportation. A systematic overview and comprehensive survey of passenger-based aircraft are investigated. The objective study is to examine fuel burn and its impact on the environment by types of aircraft. In-depth literature review studies on four pillar strategies used to design an efficient airplane. In addition, this paper also serves on advancement in evolutionary technologies used in jet transport aircraft. Reflecting the benefits and challenges of different aircraft designs technologies were also highlighted. This paper highlights the future implications and managerial insights for future aircraft designers.

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Far-field drag decomposition using hybrid formulas and vorticity based area sensors

Cited by 4 publications

References 35 publications

Energy-Based Aerodynamic Loss and Recovery Characteristics of Adiabatic and Heated Fuselages

Energy-Based Aerodynamic Loss and Recovery Characteristics of Adiabatic and Heated Fuselages

Aerodynamic Robust Design Research Using Adjoint-Based Optimization under Operating Uncertainties

Sustainable Technology on Aircraft Design: A Review

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