A Fast and Efficient Method for Multiobjective Aerodynamic Optimization of a Civil Aircraft Fuselage

Rohani, S. V.; Jahangirian, A.

doi:10.1061/(asce)as.1943-5525.0001494

Cited by 2 publications

(1 citation statement)

References 24 publications

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“…The use of modern materials, such as carbon fiber, allow a reduction in empty weight, therefore increasing the payload weight [2,7,8]. The use of modern materials also allows the shapes of the aircraft themselves to be optimized, thereby increasing their aerodynamic efficiency [9]. This makes it possible to reduce energy requirements or increase cruise speeds [10,11].…”

Section: Introductionmentioning

confidence: 99%

Aircraft piston engine load distribution in steady state operating conditions

Czarnigowski¹,

Trendak²

2023

Combustion Engines

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The article presents the results of analysis of operational parameters of piston engine CA 912 ULT which is a propulsion system of ultralight gyroplane Tercel produced by Aviation Artur Trendak. Research was conducted under normal operating conditions of the autogyro and data was collected from 15 independent tests including a total of 14 flight hours conducted during training flights. Engine and flight parameters were recorded at 9 Hz during each flight using on-board Fligh Data Recorded system. Collective results were presented to show the statistical analyses of the individual parameters by determining the mean values, standard deviations and histograms of the distribution of these parameters. The analyses included engine speed, charge pressure, air temperature, oil temperature and exhaust temperature. Histograms of operating points defined by both engine speed and manifold air pressure were also determined. Analyses were carried out to determine the contribution of steady-state and transient engine operation. It was also shown that the dynamics of engine work in real operating conditions is small. Detailed analyses were conducted for steady-state conditions. The value of the engine load index was determined and its statistical analyses were carried out. It was shown that the engine operating points are concentrated mainly in the range of idle and power above 50% of nominal power. The most frequent range is 50% to 80% of nominal power.

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Section: Introductionmentioning

confidence: 99%

Aircraft piston engine load distribution in steady state operating conditions

Czarnigowski¹,

Trendak²

2023

Combustion Engines

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Numerical two-dimensional optimization of a cylindrical fuselage for bioinspired unmanned aerial vehicle based on non-dominated sorting genetic algorithm-II

Dewangan,

Roy

2024

Proceedings of the Institution of Mechanical Engineers, Part G:

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To achieve an aerodynamically efficient design of fuselage for bioinspired unmanned aerial vehicles (UAV), the development of a systematic method is of paramount need. This work presents a multiobjective optimization study for shape parameterization of a 2D fuselage of foldable flapping wing UAV in low Reynolds number (2e05) flight conditions. The novelty of the research work lies in integrating S1223 airfoil characteristics for predicting the efficient shape design of the fuselage. This paper offers four sections; (i) the validation of the ANSYS Fluent model with experiment, (ii) the exploration of design variables using Design of Experiment (Sparse Grid Initialization), (iii) the implementation of response surface method (Genetic Aggregation) to know about dimensional sensitivity among independent and dependent variables and (iv) the application of multiobjective optimization method i.e. NSGA II to optimize the drag and lift coefficient. To identify the superiority, a comparative study between the original and optimized fuselage is presented considering many parameters like pressure contours, velocity contours, pressure coefficients, and streamlines representations. It is evident from various results that the 2D optimum shape significantly minimizes the drag coefficient and increases the lift coefficient. This work also makes room for 3D shape optimization, which helps in prototype fabrication for real-time flight conditions.

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A Fast and Efficient Method for Multiobjective Aerodynamic Optimization of a Civil Aircraft Fuselage

Cited by 2 publications

References 24 publications

Aircraft piston engine load distribution in steady state operating conditions

Aircraft piston engine load distribution in steady state operating conditions

Numerical two-dimensional optimization of a cylindrical fuselage for bioinspired unmanned aerial vehicle based on non-dominated sorting genetic algorithm-II

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