Version 1
: Received: 26 September 2023 / Approved: 27 September 2023 / Online: 28 September 2023 (03:35:07 CEST)
How to cite:
Gupta, S.; Kumar, S.; Kumar, R. Effect of Variation of Location of the Blowing on the Aerodynamic Characteristics over the Delta Wing. Preprints2023, 2023091914. https://doi.org/10.20944/preprints202309.1914.v1
Gupta, S.; Kumar, S.; Kumar, R. Effect of Variation of Location of the Blowing on the Aerodynamic Characteristics over the Delta Wing. Preprints 2023, 2023091914. https://doi.org/10.20944/preprints202309.1914.v1
Gupta, S.; Kumar, S.; Kumar, R. Effect of Variation of Location of the Blowing on the Aerodynamic Characteristics over the Delta Wing. Preprints2023, 2023091914. https://doi.org/10.20944/preprints202309.1914.v1
APA Style
Gupta, S., Kumar, S., & Kumar, R. (2023). Effect of Variation of Location of the Blowing on the Aerodynamic Characteristics over the Delta Wing. Preprints. https://doi.org/10.20944/preprints202309.1914.v1
Chicago/Turabian Style
Gupta, S., Sanjeev Kumar and Rakesh Kumar. 2023 "Effect of Variation of Location of the Blowing on the Aerodynamic Characteristics over the Delta Wing" Preprints. https://doi.org/10.20944/preprints202309.1914.v1
Abstract
The flow field around a delta wing is substantially altered by the impact of the active flow control technique. The present study involves the sharp-edged delta wing of 65 deg sweep angle with different active flow control configurations. The blowing was employed as an active flow control method on the top surface of the delta wing. The various configurations considered are the baseline delta wing, delta wing with blowing holes located at 1.62%, 3.24% and 4.86% of root chord from the leading edge to the centre of the blowing holes. The computation is performed using the commercial software ANSYS Fluent. Unsteady, incompressible Reynolds-averaged Navier-Stokes equation and the shear-stress transport k-ω turbulence model are employed. The angles of attack varied in the range of 0o < α < 35o and Reynolds number is 2.64 x106 and the jet momentum coefficient is fixed at 0.05. The blowing of air from the injection region enhances the strength of the leading-edge vortices resulting in the delay of the vortex breakdown. The performance of the delta wing is greatly improved while using the blowing method specifically for the blowing holes located at 3.24% of root chord from the leading edge as compared to without the blowing method.
Copyright:
This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
