Expected drag minimization for aerodynamic design optimization based on aircraft operational data

Liem, Rhea Patricia; Martins, Joaquim R. R. A.; Kenway, Gaetan K.

doi:10.1016/j.ast.2017.01.006

Cited by 53 publications

(24 citation statements)

References 17 publications

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“…The relative permittivity is carried out by the substrate of the patch and the thickness of the patch can be represented as t. The frequency range of patch antenna design is 1GHz. The power radiated and received from the antenna is depends on the radial distance and angular position [26][27][28][29][30]. The patch antenna length can be evaluated by [31][32][33],…”

Section: Designmentioning

confidence: 99%

Conformal Antenna for Aerodynamic Drag Reduction in Airborne System

Namrutha¹,

Raaza²,

Ramesh³

2018

IJET

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The conformal antenna receives more consideration towards the coverage augmentation of contemporary wireless communication systems. The foremost unprejudiced of conformal antenna is to reduce aerodynamic drag in aircraft. Consequently designing frequency reconfigurable conformal antenna has become a key concern in the airborne system. This article reviews the state-of-the-art conformal antenna design by considering the challenges of reducing the aerodynamic drag in the airborne applications. Microstrip patch antennas represent compact antenna that offer a conformal nature and capability of equipped integration with communication system. In this work, microstrip patch antenna is designed for airborne system for drag reduction. The hybrid particle swarm and cuckoo search optimization algorithm is utilized for the length and width. Then the algorithm values are used for the calculation of effective length. The performance of the proposed method is compared with hybrid artificial neural network and firefly, genetic algorithm and analyzed.

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Section: Designmentioning

confidence: 99%

Conformal Antenna for Aerodynamic Drag Reduction in Airborne System

Namrutha¹,

Raaza²,

Ramesh³

2018

IJET

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“…The first is that to apply it successfully requires careful selection of both the design points (these are often known a priori but can be determined using gradient span analysis [27]), and the weightings between the objectives at those design points. This issue can be eased by using automated weight selections [28,29], an integral approach [30] or a probabilistic approach [31]. The second common issue is the cost surrounding multi-point optimization.…”

Section: Introductionmentioning

confidence: 99%

Comparison of Point Design and Range-Based Objectives for Transonic Aerofoil Optimization

2018

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The most common aerofoil optimization problem considered is lift-constrained drag minimization at a fixed design point, however, shock-free solutions can result which can lead to poor off-design performance. As such, this paper presents a study into the construction of the aerofoil optimization problem and its effect of the performance over a range of operating conditions. Single-and multi-point optimizations of aerofoils in transonic flow are considered and an improved range-based optimization problem subject to a constraint on fixed non-dimensional wing loading with a varying design point is formulated. This problem is more representative of the aircraft design problem though similar in cost to single-point drag minimization. An analytical treatment using an approximation of wave drag is also presented which demonstrates that the optimum Mach number for a fixed shape is supercritical if the required loading is above a critical threshold. Optimizations are presented that show that to define an effective objective function, three-dimensional effects modelled via an induced drag term must be introduced. The general trend is to produce solutions with higher Mach numbers and lower lift coefficients, and that shocked solutions perform better when considering the performance in range over the operating space. Furthermore, the resulting aerofoil shapes are supercritical in nature; a particularly promising result. Nomenclature a, b Linear surface pressure coefficient approximation constants

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“…Such problems arise broadly in chemical process design, structural design, renewable energy systems, portfolio optimization, stochastic model predictive control, discrete event systems, and many other applications. Moreover, although we restrict our attention to single‐stage problems in this article (i.e., problems with no recourse decisions), more flexible two‐stage and multistage formulations can also be reduced to Problem (1) through the use of parameterized decision rules, which is an increasingly popular method for obtaining tractable approximate solutions …”

Section: Introductionmentioning

confidence: 99%

“…In the applications above, many uncertainties are best modeled by continuous random variables, including process yields, material properties, renewable power generation, product demands, returns on investments, and so forth . However, when f is nonlinear with respect to

bold-italicω

, this very often precludes writing the function

F (x) \equiv E [f (x, ω)]

analytically in closed form.…”

Section: Introductionmentioning

confidence: 99%

Convex relaxations for global optimization under uncertainty described by continuous random variables

Shao

Scott

2018

AIChE Journal

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This article considers nonconvex global optimization problems subject to uncertainties described by continuous random variables. Such problems arise in chemical process design, renewable energy systems, stochastic model predictive control, etc. Here, we restrict our attention to problems with expected-value objectives and no recourse decisions. In principle, such problems can be solved globally using spatial branch-and-bound (B&B). However, B&B requires the ability to bound the optimal objective value on subintervals of the search space, and existing techniques are not generally applicable because expected-value objectives often cannot be written in closed-form. To address this, this article presents a new method for computing convex and concave relaxations of nonconvex expected-value functions, which can be used to obtain rigorous bounds for use in B&B. Furthermore, these relaxations obey a secondorder pointwise convergence property, which is sufficient for finite termination of B&B under standard assumptions. Empirical results are shown for three simple examples.

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Expected drag minimization for aerodynamic design optimization based on aircraft operational data

Cited by 53 publications

References 17 publications

Conformal Antenna for Aerodynamic Drag Reduction in Airborne System

Conformal Antenna for Aerodynamic Drag Reduction in Airborne System

Comparison of Point Design and Range-Based Objectives for Transonic Aerofoil Optimization

Convex relaxations for global optimization under uncertainty described by continuous random variables

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