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Multi-Objective Optimization of Transonic Variable Camber Airfoil with Leading- and Trailing-Edge Deflections Using Kriging Surrogate Model

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Publicado en:Aerospace vol. 12, no. 8 (2025), p. 659-683
Autor principal: Wang, Wei
Otros Autores: He, Feng, Cui Shenao, Li Zhandong
Publicado:
MDPI AG
Materias:
National Aeronautics & Space Administration > NASA
Software
Accuracy
Drag coefficients
Trailing edges
Investigations
Aerodynamic coefficients
Optimization techniques
Camber
Airfoils
Pressure distribution
Multiple objective analysis
Sorting algorithms
Pareto optimum
Aerodynamic characteristics
Efficiency
Aircraft
Drag
Deflection
Design optimization
Genetic algorithms
Evolution & development
Prediction models
Mach number
Aerodynamics
Neural networks
Optimization
Critical angle
Variables
Angle of attack
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Resumen:To investigate the aerodynamic characteristics and multi-objective optimization of the variable camber airfoils, the influence of leading- and trailing-edge deflections on aerodynamic performance is conducted. A novel prediction model is presented using the Kriging surrogate model, with leading and trailing edge deflection angles as inputs and lift coefficients and drag coefficients as outputs. The Non-dominated Sorting Genetic Algorithm II (NSGA II) multi-objective optimization technique is applied to ascertain the ideal deflection parameters. The results show that upward deflection of the leading edge raises the lift, whereas downward deflection increases the value of the critical angle of attack. The deflection of the trailing edge increases the value of the critical angle of attack, while the downward deflection can enhance the lift coefficient. Appropriate upward deflections of both leading and trailing edges can delay the critical Mach number, while downward deflections of both the leading and trailing edges can enhance the value of the critical Mach number. The discrepancies between the Kriging model prediction and the CFD simulation are less than 2%. Compared to the basic airfoil, the aerodynamic performance of the optimized airfoil has been improved, with the lift coefficient increasing by 7.55% and 7.37% and the lift-to-drag ratio rising by 6.97% and 10.27% at two Mach numbers, respectively. The efficiency and reliability of this method have been verified.
ISSN:2226-4310
DOI:10.3390/aerospace12080659
Fuente:Advanced Technologies & Aerospace Database