Optimization of Airfoils for Minimum Pitching Moment and Compressibility Drag Coefficients

Farrokhfal, Hamid; Pishevar, Ahmadreza

doi:10.5028/jatm.v6i4.403

Cited by 5 publications

(6 citation statements)

References 16 publications

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“…As well in Fig. 3 is presented also the trend of the pressure coefficient, on the suction side, compared with the experimental data of Farrokhnal et al [12]. The trend is well reproduced comparing it with the experimental data, where the slight difference is due to the inviscid flow assumption.…”

Section: Bidimensional Naca 0012 Airfoilsupporting

confidence: 76%

Development of a robust solver to model the flow inside the engines for high-speed propulsion

Nista

Saracoglu

2019

MATEC Web Conf.

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The demand for discovering new commercial routes as well as the possibility to shortening civilian long-haul flights boosted the interest of civil hypersonic vehicle designs. Among all the multiple projects started by the various nations, the European community funded project STRATOFLY aims at refining the baseline LAPCAT II-MR2.4 design for further improvements. The new aircraft would enable a flight shorter that 3 hours from Brussels to Sydney, carrying 300-passengers above the already crowed atmosphere. The wide Mach range operability, up to Mach 8, demands the use of multiple engines, leading to a highly integrated propulsion system. The current study is focused on the development of new CFD platform to estimate the performance of the combined propulsion system during the supersonic to hypersonic transition. In order to control the complex flow physics, highfidelity CFD simulations remain the fundamental tools for the preliminary investigations. On the current framework, an advanced robust compressible solver has been develop d in order to handle the different flow regimes. The new tool solves Unsteady Reynolds-Averaged Navier-Stokes (URANS) equations by employing cell-centered Finite Volume Method constructed on openFoam toolbox. Two innovative high-order discretization schemes, with different abilities, based on approximated Riemann solvers were developed for capturing the flow physics within high-speed propulsion systems. Advanced time discretization has been taken into account to increase the temporal accuracy. At the end, the whole implementation has been validated in multiple test cases, ranging from incompressible to hypersonic regimes, confirming its excellent stability, robustness and accuracy.

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Section: Bidimensional Naca 0012 Airfoilsupporting

confidence: 76%

Development of a robust solver to model the flow inside the engines for high-speed propulsion

Nista

Saracoglu

2019

MATEC Web Conf.

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“…It is well known that the adjoint method based on the macroscopic equations, that is, NS or Euler equations has been completely developed for shape optimization. For example, Farrokhfal et al 27,28 applied the adjoint algorithm based on the Euler equation for optimization of the rotor blade section and planform.…”

Section: Introductionmentioning

confidence: 99%

“…We recently developed a novel adjoint formulation and algorithm based on compressible LBM (Circular Function scheme) for the flow optimization in smoothed and discontinues flow. 28 In this paper, a robust optimization algorithm is extended based on combination of the adjoint method and LBM for airfoil shape optimization for the first time. Thus, the developed code uses advantages of the LBM and also the capabilities of the adjoint method in aerodynamic shape optimization.…”

Section: Introductionmentioning

confidence: 99%

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Airfoil inverse design based on laminar compressible adjoint lattice Boltzmann method

Khouzani

Kamali-Moghadam

2023

Numerical Methods in Fluids

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A new optimization techniques based on the adjoint lattice Boltzmann method is derived for airfoil inverse design in laminar compressible flows. In this study, the developed adjoint lattice Boltzmann scheme based on the circular function (CF) is extended for airfoil inverse design problems in laminar incompressible and compressible flows. New mathematical derivation based on compressible lattice Boltzmann equations (LBE) is developed which can find target shape of an airfoil with available desired pressure distribution. The adjoint lattice Boltzmann method is extended for both the incompressible and compressible flows by selecting the circular function idea for calculating the equilibrium distribution functions. So, the adjoint equation is also expanded based on CF idea for calculation of objective function gradient vector. The steepest decent technique is utilized as gradient optimizer. Also, a novel solution is presented to remove singularity problem of the adjoint boundary condition. In order to validate the developed optimization algorithm, results are presented for both incompressible and compressible inverse problem in steady and unsteady flow and accurate results are obtained.

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“…equations. Pishevar et al (2013) and Farrokhfal et al (2014) applied the adjoint method with the Euler equation for optimization of the rotor blade and its plan form. Leoviriyakit (2005) derived the adjoint scheme based on the RANS equations and applied it on airfoil and wing plan form optimization.…”

Section: Introductionmentioning

confidence: 99%

Wave Drag Reduction of SC(2)0410 Airfoil using New Developed Inviscid Compressible Adjoint Method

2020

JAFM

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A supercritical airfoil is geometrically optimized using the new developed adjoint compressible lattice Boltzmann method. Minimizing the drag coefficient and eliminating the shock wave on the supercritical airfoil surface are considered as the cost function with constraint of fixed lift coefficient. The continuous adjoint method is applied to able designers to implement large number of design variables in actual optimization problems. The adjoint equation based on the specified cost function and constrains is successfully derived. Discretization of the governing equations is carried out using the finite volume approach and 3 rd order of the MUSCL scheme. The supercritical SC(2)0410 airfoil, which has a strong shock on the top surface at transonic cruise conditions, is numerically optimized using the inviscid developed algorithm to eliminate the shock and reduce the wave drag. To validate the obtained results and show viscosity effect on the results, the base airfoil and optimized one are experimentally tested in a transonic wind tunnel at the same conditions. Pressure distribution on the surface of both the base and optimal airfoil are extracted from the experimental tests and compared with those of numerical simulations. The results indicate that the developed approach can be properly used for supercritical airfoil shape optimization for elimination the shock and reduction the wave drag.

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Optimization of Airfoils for Minimum Pitching Moment and Compressibility Drag Coefficients

Cited by 5 publications

References 16 publications

Development of a robust solver to model the flow inside the engines for high-speed propulsion

Development of a robust solver to model the flow inside the engines for high-speed propulsion

Airfoil inverse design based on laminar compressible adjoint lattice Boltzmann method

Wave Drag Reduction of SC(2)0410 Airfoil using New Developed Inviscid Compressible Adjoint Method

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