Numerical Analysis of Transonic Performance of a Compound Delta Wing
Disciplines
Aerodynamics and Fluid Mechanics
Abstract (300 words maximum)
Transonic flight holds paramount significance in the domain of global air forces. The efficacy of delta wings in supersonic flow conditions has been widely acknowledged. This success is primarily attributed to their low wing thickness, which serves to mitigate wave drag. But fighter aircraft mainly operate and maneuver at transonic speeds. Additionally, delta wings exhibit a vortex lift phenomenon, stemming from the generation of leading-edge vortices at elevated angles of attack. Consequently, since the 1950s, military aircraft have extensively employed delta wing configurations. While maneuvering at transonic speeds delta wings encounter a phenomenon termed vortex breakdown at heightened angles of attack. Vortex breakdown manifests as the rupture of leading-edge vortices, resulting in diminished lift and altered aerodynamic behavior. This research endeavors to deepen our comprehension of vortex breakdown evolution over a compound delta wing configuration. Numerical simulations were employed to scrutinize the flow dynamics over the wing. These simulations encompassed a Mach number range spanning from 0.6 to 1.0, coupled with angles of attack varying from 0° to 15°. The simulations were executed utilizing Reynolds-Averaged Navier–Stokes transient computations due to the flows unsteady nature, supplemented by the Spalart-Allmaras turbulence model. The findings reveal that compound delta wings exhibit vortex breakdown, particularly at elevated angles of attack. This investigation contributes essential insights into the mechanisms underlying vortex breakdown over compound delta wings, laying the groundwork for future investigations aimed at devising strategies to delay vortex breakdown and control its formation.
Academic department under which the project should be listed
SPCEET - Mechanical Engineering
Primary Investigator (PI) Name
Gaurav Sharma
Numerical Analysis of Transonic Performance of a Compound Delta Wing
Transonic flight holds paramount significance in the domain of global air forces. The efficacy of delta wings in supersonic flow conditions has been widely acknowledged. This success is primarily attributed to their low wing thickness, which serves to mitigate wave drag. But fighter aircraft mainly operate and maneuver at transonic speeds. Additionally, delta wings exhibit a vortex lift phenomenon, stemming from the generation of leading-edge vortices at elevated angles of attack. Consequently, since the 1950s, military aircraft have extensively employed delta wing configurations. While maneuvering at transonic speeds delta wings encounter a phenomenon termed vortex breakdown at heightened angles of attack. Vortex breakdown manifests as the rupture of leading-edge vortices, resulting in diminished lift and altered aerodynamic behavior. This research endeavors to deepen our comprehension of vortex breakdown evolution over a compound delta wing configuration. Numerical simulations were employed to scrutinize the flow dynamics over the wing. These simulations encompassed a Mach number range spanning from 0.6 to 1.0, coupled with angles of attack varying from 0° to 15°. The simulations were executed utilizing Reynolds-Averaged Navier–Stokes transient computations due to the flows unsteady nature, supplemented by the Spalart-Allmaras turbulence model. The findings reveal that compound delta wings exhibit vortex breakdown, particularly at elevated angles of attack. This investigation contributes essential insights into the mechanisms underlying vortex breakdown over compound delta wings, laying the groundwork for future investigations aimed at devising strategies to delay vortex breakdown and control its formation.