Analysis of Vortex Breakdown Over Compound Delta Wings
Disciplines
Aerodynamics and Fluid Mechanics | Aerospace Engineering | Engineering
Abstract (300 words maximum)
The phenomenon of vortex flow formation inherent to the compound delta wing geometry facilitates lift generation on the wing. At a specific angle of attack, the vortices undergo breakdown, resulting in a complete cessation of lift generation. It is widely acknowledged that vortex breakdown typically occurs within the range of 10 to 15 degrees, precipitating a significant decline in the lift coefficient. This phenomenon poses a considerable hazard to aircraft, potentially leading to mid-air stall events. Precisely determining this critical threshold is imperative for comprehending the behavior of the delta wing across both supersonic and subsonic flows.
A combination of SolidWorks for geometry creation and Ansys Fluent for preliminary simulations is employed to elucidate this critical threshold. Leveraging the computational capabilities of Ansys Fluent, particularly through the utilization of continuity and momentum equations, is anticipated to yield comprehensive insights into the flow field encompassing the compound delta wing. The iterative execution of simulations encompassing various angles of attack aims to pinpoint the formation and breakdown of vortices, thereby interpreting lift and drag coefficients, alongside other pertinent data essential for identifying the critical threshold associated with this phenomenon.
Academic department under which the project should be listed
SPCEET - Mechanical Engineering
Primary Investigator (PI) Name
Gaurav Sharma
Analysis of Vortex Breakdown Over Compound Delta Wings
The phenomenon of vortex flow formation inherent to the compound delta wing geometry facilitates lift generation on the wing. At a specific angle of attack, the vortices undergo breakdown, resulting in a complete cessation of lift generation. It is widely acknowledged that vortex breakdown typically occurs within the range of 10 to 15 degrees, precipitating a significant decline in the lift coefficient. This phenomenon poses a considerable hazard to aircraft, potentially leading to mid-air stall events. Precisely determining this critical threshold is imperative for comprehending the behavior of the delta wing across both supersonic and subsonic flows.
A combination of SolidWorks for geometry creation and Ansys Fluent for preliminary simulations is employed to elucidate this critical threshold. Leveraging the computational capabilities of Ansys Fluent, particularly through the utilization of continuity and momentum equations, is anticipated to yield comprehensive insights into the flow field encompassing the compound delta wing. The iterative execution of simulations encompassing various angles of attack aims to pinpoint the formation and breakdown of vortices, thereby interpreting lift and drag coefficients, alongside other pertinent data essential for identifying the critical threshold associated with this phenomenon.