Optimization of SD7003 airfoil performance using TBL and CBL at low Reynolds numbers

Kamari, Dj.; Tadjfar, Mehran; Madadi, Ali

doi:10.1016/j.ast.2018.05.049

Cited by 33 publications

(16 citation statements)

References 24 publications

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“…The method is widely used in the optimization process for engineering applications and has proven to be an efficient optimization process in the field of aerospace engineering as well. 32 genetic algorithm applications have been successfully employed in a number of studies on spacecraft controls, 33 flight trajectories, 34 airfoil, 35,36 and propellers. 37 For the present study, we preferred GA over gradient-based optimization so that the global maxima for pressure recovery could be identified instead of any local optima.…”

Section: Surrogate Modelingmentioning

confidence: 99%

Design and optimization of bump (compression surface) for diverterless supersonic inlet

Arif

Iftikhar

Javed

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this article design and optimization scheme of a three-dimensional bump surface for a supersonic aircraft is presented. A baseline bump and inlet duct with forward cowl lip is initially modeled in accordance with an existing bump configuration on a supersonic jet aircraft. Various design parameters for bump surface of diverterless supersonic inlet systems are identified, and design space is established using sensitivity analysis to identify the uncertainty associated with each design parameter by the one-factor-at-a-time approach. Subsequently, the designed configurations are selected by performing a three-level design of experiments using the Box–Behnken method and the numerical simulations. Surrogate modeling is carried out by the least square regression method to identify the fitness function, and optimization is performed using genetic algorithm based on pressure recovery as the objective function. The resultant optimized bump configuration demonstrates significant improvement in pressure recovery and flow characteristics as compared to baseline configuration at both supersonic and subsonic flow conditions and at design and off-design conditions. The proposed design and optimization methodology can be applied for optimizing the bump surface design of any diverterless supersonic inlet system for maximizing the intake performance.

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Section: Surrogate Modelingmentioning

confidence: 99%

Design and optimization of bump (compression surface) for diverterless supersonic inlet

Arif

Iftikhar

Javed

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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show abstract

“…The influence of jet location on lift was remarkable at α = 20 • , with up to 57% increase, but not so noticeable at 18 • . Kamari et al [40] optimised constant blowing and constant suction on the SD7003 airfoil at Re = 6 × 10 4 by coupling Genetic Algorithms (GA) with Artificial Neural Networks (ANN) previously trained with a set of almost 45 CFD runs. Optimal constant suction was shown more effective.…”

Section: Introductionmentioning

confidence: 99%

Large Eddy Simulation of optimal Synthetic Jet Actuation on a SD7003 airfoil in post-stall conditions

Tousi

Bergadà

Mellibovsky

2022

Aerospace Science and Technology

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“…The results proved that ANN could predict the flow parameters reasonably well, and ANN can reduce by several orders of magnitude the time for optimizing these flow parameters. ANN was also coupled with a genetic algorithm by Kamari [16] to optimize the Selig-Donovan 7003 (SD7003) airfoil aerodynamic performance by finding optimum parameters of blowing/suction. Optimization results showed that a significant reduction of the separation zone was achievable.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation and Hydrodynamic Performance Predicting of 2 Two-Dimensional Hydrofoils in Tandem Configuration

Shang

Horrillo

2021

JMSE

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In this study we investigated the performance of NACA 0012 hydrofoils aligned in tandem using parametric method and Neural Networks. We use the 2D viscous numerical model (STAR-CCM+) to simulate the hydrofoil system. To validate the numerical model, we modeled a single NACA 0012 configuration and compared it to experimental results. Results are found in concordance with the published experimental results. Then two NACA 0012 hydrofoils in tandem configuration were studied in relation to 788 combinations of the following parameters: spacing between two hydrofoils, angle of attack (AOA) of upstream hydrofoil and AOA of downstream hydrofoil. The effects exerted by these three parameters on the hydrodynamic coefficients Lift coefficient (CL), Drag Coefficient (CD) and Lift-Drag Ratio (LDR), are consistent with the behavior of the system. To establish a control system for the hydrofoil craft, a timely analysis of the hydrodynamic system is needed due to the computational resource constraints, analysis of a large combination and time consuming of the three parameters established. To provide a broader and faster way to predict the hydrodynamic performance of two hydrofoils in tandem configuration, an optimal artificial neural network (ANN) was trained using the large combination of three parameters generated from the numerical simulations. Regression analysis of the output of ANN was performed, and the results are consistent with numerical simulation with a correlation coefficient greater than 99.99%. The optimized spacing of 6.6c are suggested where the system has the lowest CD while obtaining the highest CL and LDR. The formula of the ANN was then presented, providing a reliable predicting method of hydrofoils in tandem configuration.

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Optimization of SD7003 airfoil performance using TBL and CBL at low Reynolds numbers

Cited by 33 publications

References 24 publications

Design and optimization of bump (compression surface) for diverterless supersonic inlet

Design and optimization of bump (compression surface) for diverterless supersonic inlet

Large Eddy Simulation of optimal Synthetic Jet Actuation on a SD7003 airfoil in post-stall conditions

Numerical Simulation and Hydrodynamic Performance Predicting of 2 Two-Dimensional Hydrofoils in Tandem Configuration

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