What is it about?
Shock oscillations in transonic flight over an airplane wing are caused due to the part chord shock over the wing inducing flow separation in the boundary layer close to the surface of the wing. Shock oscillations occur due to a a combination of angle of attack of the wing with reference to the free stream flow, Mach number of the free stream flow, the Reynolds number, and the shape of the cross-section of the wing.
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Why is it important?
Transonic buffet leads to unsteady airloads over the wing. This in turn could cause fatigue on the wing structure leading to failure. Since most commercial airliners cruise at transonic Mach numbers, this phenomenon is important to understand so that it can be controlled or even eliminated.
Perspectives
These are URANS simulations carefully done with a time-step of 10^(-7) sec at an angle of attack of 5 deg at a Mach number of 0.85. The flow is fully turbulent.
Kartik Venkatraman
Indian Institute of Science
Read the Original
This page is a summary of: Shock vortex interactions and transonic buffet over a delta wing, June 2022, American Institute of Aeronautics and Astronautics (AIAA),
DOI: 10.2514/6.2022-4173.
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