Discrete Adjoint Based Optimal Active Control of Separation on a Realistic High-Lift Configuration

2016 ◽  
pp. 237-246 ◽  
Author(s):  
Anil Nemili ◽  
Emre Özkaya ◽  
Nicolas R. Gauger ◽  
Felix Kramer ◽  
Frank Thiele
Keyword(s):  
Active Control ◽  
High Lift ◽  
Discrete Adjoint

Discrete Adjoint based Sensitivity Analysis for Optimal Flow Control of a 3D High-Lift Configuration

2013 ◽  
Author(s):  
Anil Nemili ◽  
Özkaya Emre ◽  
Nicolas R. Gauger ◽  
Felix W. Kramer ◽  
Angelo Carnarius ◽  
...  
Keyword(s):  
Sensitivity Analysis ◽  
Flow Control ◽  
High Lift ◽  
Optimal Flow ◽  
Discrete Adjoint ◽  
Optimal Flow Control

Discrete Adjoint based Sensitivity Analysis for Optimal Active Flow Control of High-Lift Configurations

PAMM ◽  
2013 ◽  
Vol 13 (1) ◽  
pp. 347-348
Author(s):  
Anil Nemili ◽  
Emre Özkaya ◽  
Nicolas Gauger
Keyword(s):  
Sensitivity Analysis ◽  
Flow Control ◽  
Active Flow Control ◽  
High Lift ◽  
Discrete Adjoint ◽  
Active Flow

scholarly journals Aerodynamic Shape Optimisation of a Camber Morphing Airfoil and Noise Estimation

Aerospace ◽  
2022 ◽  
Vol 9 (1) ◽  
pp. 43
Author(s):  
Robert Valldosera Martinez ◽  
Frederico Afonso ◽  
Fernando Lau
Keyword(s):  
Lift Coefficient ◽  
Shape Optimisation ◽  
Structural Constraints ◽  
High Lift ◽  
Airframe Noise ◽  
Pressure Distributions ◽  
Discrete Adjoint ◽  
Coefficient Increase ◽  
Gradient Based ◽  
Optimisation Procedure

In order to decrease the emitted airframe noise by a two-dimensional high-lift configuration during take-off and landing performance, a morphing airfoil has been designed through a shape design optimisation procedure starting from a baseline airfoil (NLR 7301), with the aim of emulating a high-lift configuration in terms of aerodynamic performance. A methodology has been implemented to accomplish such aerodynamic improvements by means of the compressible steady RANS equations at a certain angle of attack, with the objective of maximising its lift coefficient up to equivalent values regarding the high-lift configuration, whilst respecting the imposed structural constraints to guarantee a realistic optimised design. For such purposes, a gradient-based optimisation through the discrete adjoint method has been undertaken. Once the optimised airfoil is achieved, unsteady simulations have been carried out to obtain surface pressure distributions along a certain time-span to later serve as the input data for the aeroacoustic prediction framework, based on the Farassat 1A formulation, where the subsequent results for both configurations are post-processed to allow for a comparative analysis. Conclusively, the morphing airfoil has proven to be advantageous in terms of aeroacoustics, in which the noise has been reduced with respect to the conventional high-lift configuration for a comparable lift coefficient, despite being hampered by a significant drag coefficient increase due to stall on the morphing airfoil’s trailing edge.

Performance Evaluation of Linear Oscillatory Actuator for Active Control Engine Mount

2012 ◽  
Vol 132 (12) ◽  
pp. 1091-1096 ◽  
Author(s):  
Fumiya Kitayama ◽  
Katsuhiro Hirata ◽  
Yasuyoshi Asai
Keyword(s):  
Performance Evaluation ◽  
Active Control ◽  
Engine Mount
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