Genetic optimization of target pressure distributions for inverse design methods

AIAA Journal ◽  
1996 ◽  
Vol 34 (5) ◽  
pp. 881-886 ◽  
Author(s):  
Shigeru Obayashi ◽  
Susumu Takanashi
Keyword(s):  
Design Methods ◽  
Inverse Design ◽  
Genetic Optimization ◽  
Pressure Distributions ◽  
Target Pressure

Inverse Design of Airfoils Using Target Pressure Optimization

2013 ◽  
Vol 694-697 ◽  
pp. 3183-3188
Author(s):  
Ya Feng Liu ◽  
Dong Li Ma
Keyword(s):  
Genetic Algorithm ◽  
Laminar Flow ◽  
Design Method ◽  
Spline Interpolation ◽  
Inverse Design ◽  
Spline Functions ◽  
Control Points ◽  
B Spline ◽  
Pressure Distributions ◽  
Target Pressure

The Direct Iterative Surface Curvature (DISC) airfoil design method developed by NASA Langley, which is one of the inverse design methods, is robust and effective. In order to determine the target pressure distributions of airfoils, this paper used the uniformed B-spline interpolation for the parameterization of the target pressure, and a Genetic Algorithm (GA) was used to optimize the coordinates of the control points of the B-spline functions. Two cases were given to prove the effect of the DISC design method. A laminar flow airfoil was then designed using DISC after a target pressure had been determined by a GA. Results show that the DISC method based on target pressure optimization using GAs is pretty effective.

Aerodynamic Design of S-Shaped Diffusers Using Ball Spine Inverse Design Method

2014 ◽  
Author(s):  
Ali Madadi ◽  
Mahdi Nili-Ahmadabadi ◽  
Mohammad Jafar Kermani
Keyword(s):  
Design Method ◽  
Inverse Design ◽  
Cross Sectional ◽  
Design Algorithm ◽  
Flow Solver ◽  
Pressure Distributions ◽  
Duct Geometry ◽  
Sst Turbulence Model ◽  
Target Pressure ◽  
Inverse Design Method

Recently, an inverse design algorithm called ball-spine algorithm (BSA) is introduced for the design of 2-D ducts. In this approach, the walls are considered as a set of virtual balls that can freely move along the straight directions called spines. In the present work the method is developed for quasi 3-D design of S-shaped ducts with a predefined width. To do so, the upper and lower lines of the S-duct symmetric section are modified under the BSA and then, the 3-D S-duct geometry is obtained based on elliptic cross sectional profiles. The target pressure distributions along the upper and lower lines are prescribed so that the separation does not occur. Finally, the flow through the designed S-duct is numerically analyzed using a viscous flow solver with the SST turbulence model to validate the designed S-duct performance.

Dual Point Redesign of an Axial Compressor Airfoil Using a Viscous Inverse Design Method

2010 ◽  
Author(s):  
Raja Ramamurthy ◽  
Wahid Ghaly
Keyword(s):  
Performance Improvement ◽  
Stokes Equations ◽  
Design Method ◽  
Weighted Average ◽  
Inverse Design ◽  
Pressure Distributions ◽  
Target Pressure ◽  
The Difference ◽  
Inverse Design Method ◽  
Operating Points

The midspan section of Rotor 67 is redesigned simultaneously at two different design points using a new inverse blade design method where the blade walls move with a virtual velocity distribution derived from the difference between the current and the target pressure distributions on the blade surfaces. This inverse method is fully consistent with the viscous flow assumption and is implemented into the time accurate solution of the Reynolds-Averaged Navier-Stokes equations that are expressed in an arbitrary Lagrangian-Eulerian (ALE) form to account for mesh movement. A cell-vertex finite volume method of the Jameson type is used to discretize the equations in space; time accurate integration is obtained using dual time stepping. An algebraic Baldwin-Lomax turbulence model is used for turbulence closure. The CFD analysis provides the initial blade pressure distributions at both operating points, e.g. at two different back pressures and/or blade speeds. At each operating point, a target pressure distribution that results in a performance improvement, is prescribed. The inverse design method is then used to reach the prescribed target pressure distributions at both operating points, simultaneously. This is done by using a weighted average of the difference between the target and current pressure distributions at the two operating points, to modify the airfoil profile. The results show that by carefully tailoring the target pressure loadings at the two design points, some performance improvement can be achieved over the entire range between the two operating points.

scholarly journals Aerodynamic Inverse Design of Transonic Compressor Cascades with Stabilizing Elastic Surface Algorithm

2021 ◽  
Vol 11 (11) ◽  
pp. 4845
Author(s):  
Mohammad Hossein Noorsalehi ◽  
Mahdi Nili-Ahmadabadi ◽  
Seyed Hossein Nasrazadani ◽  
Kyung Chun Kim
Keyword(s):  
Design Method ◽  
Inverse Design ◽  
Normal Shock ◽  
Compressor Cascade ◽  
Elastic Surface ◽  
Transonic Compressor ◽  
Pressure Distributions ◽  
The Difference ◽  
Inverse Design Method ◽  
Transonic Cascade

The upgraded elastic surface algorithm (UESA) is a physical inverse design method that was recently developed for a compressor cascade with double-circular-arc blades. In this method, the blade walls are modeled as elastic Timoshenko beams that smoothly deform because of the difference between the target and current pressure distributions. Nevertheless, the UESA is completely unstable for a compressor cascade with an intense normal shock, which causes a divergence due to the high pressure difference near the shock and the displacement of shock during the geometry corrections. In this study, the UESA was stabilized for the inverse design of a compressor cascade with normal shock, with no geometrical filtration. In the new version of this method, a distribution for the elastic modulus along the Timoshenko beam was chosen to increase its stiffness near the normal shock and to control the high deformations and oscillations in this region. Furthermore, to prevent surface oscillations, nodes need to be constrained to move perpendicularly to the chord line. With these modifications, the instability and oscillation were removed through the shape modification process. Two design cases were examined to evaluate the method for a transonic cascade with normal shock. The method was also capable of finding a physical pressure distribution that was nearest to the target one.

scholarly journals Inverse Design Methods: Inverse Design Strategies for 3D Surfaces Formed by Mechanically Guided Assembly (Adv. Mater. 14/2020)

2020 ◽  
Vol 32 (14) ◽  
pp. 2070107
Author(s):  
Zhichao Fan ◽  
Yiyuan Yang ◽  
Fan Zhang ◽  
Zheng Xu ◽  
Hangbo Zhao ◽  
...  
Keyword(s):  
Design Methods ◽  
Inverse Design ◽  
Design Strategies ◽  
Guided Assembly ◽  
3D Surfaces

Inverse Design of Transonic Wings Using Wing Planform and Target Pressure Optimization

2001 ◽  
Vol 38 (4) ◽  
pp. 644-652 ◽  
Author(s):  
Taisul Ahn ◽  
Hyoung-Jin Kim ◽  
Chongam Kim ◽  
Oh-Hyun Rho
Keyword(s):  
Inverse Design ◽  
Target Pressure
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