Optimization of Injection System to Effective Control Boundary Layer Over an Aircraft Wing

This research work was carried out to identify the optimum injection location to enhance the aerodynamic performance of an aircraft wing. The three-dimensional numerical study was conducted for NACA 6321 aerofoil using k omega SST turbulence model with Reynolds Average Navier stokes equations. The r...

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Bibliographic Details
Published in2024 Parul International Conference on Engineering and Technology (PICET) pp. 1 - 4
Main Authors Rameshbhai, Patel Ankitkumar, Patidar, Vijay Kumar, K, Balaji
Format Conference Proceeding
LanguageEnglish
Published IEEE 03.05.2024
Subjects
Aerodynamics
Aerospace control
Aircraft
Airfoil
Boundary layer
Control systems
Drag Coefficient
Lift coefficient
Maintenance
Mathematical models
Numerical models
Optimization
Over-the-top media services
Solid modeling
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Summary:This research work was carried out to identify the optimum injection location to enhance the aerodynamic performance of an aircraft wing. The three-dimensional numerical study was conducted for NACA 6321 aerofoil using k omega SST turbulence model with Reynolds Average Navier stokes equations. The results show that the lift coefficient increases up to 9% and the drag coefficient decreases up to 12 % compared to the baseline aerofoil. The novelty of the proposed work is identifying the optimum injection location to enhance the performance instead of the traditional co-flow jet method. This method can be applicable for all fixed-wing aircraft vehicles to enhance the aerodynamic performance with decreasing drag.
DOI:10.1109/PICET60765.2024.10716163