A numerical study on aerodynamic wake flow control over airfoils by micro jet actuators

Prawin, L.; Rose, Jeremy

doi:10.1504/ijesms.2017.087554

Cited by 1 publication

(1 citation statement)

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“…Cattafesta and Sheplak [15] classified the various types of actuators based on their specifications (Fluidic, plasma, etc. ), design and aeronautical applications Prawin and Rose [16], announced that the maximum drag reduction obtained on the NACA6-series aerofoil configuration (NACA 63-XX8) with installed MJ actuators was about 20% at 0 °AOA. For the past ninety years of research work on active control devices, no significant contributions have been attempted over aircraft applications due to technical challenges and the installation of additional systems.…”

Section: Introductionmentioning

confidence: 99%

Streamline Effect Improvement of Additive Manufactured Airfoil Utilizing Dynamic Stream Control Procedure

Srinath

Mukesh²,

Poojari

et al. 2022

Advances in Materials Science and Engineering

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In the era of fast transport, to create inventive stream ow management solutions that are capable of diminishing the aerodynamic drag of the vehicles, there is a need to modify the ow characteristics over the vehicle by deferring or expelling the position of the ow partition. e objective of this study involves the parameterized design of an airfoil utilizing the Bezier curve technique with the assistance of the simulation program. For ow regulations, synthetic jet modules are ingrained at di erent percentages of the chord to manage the stall characteristics. e parametrization system, combined with the stream control method, can give a much better insight into ow re-energization and pave some way for the reduction of the wake. Digital fabrication technique (3d printing or Rapid Prototyping method) is used to fabricate the end product for aerodynamic testing. e comparative outcome showed a reduction in drag at certain angles of attack due to the surface nish obtained. By comparing the results, the aerodynamic e ciency showed a signi cant rise of 13.05% at lower angles of attack when compressed gas was used in the synthetic jet closer to the frontier edge of the airfoil. Near the stall angle of attack, the coe cient of lift (Cl) and coe cient of drag (Cd) values showed no progress.

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Section: Introductionmentioning

confidence: 99%