Thermal control of transonic shock-boundary layer interaction over a natural laminar flow airfoil

What is it about?

The paper explains how the unsteady shock noted for transonic flow over the SHM1 airfoil can be controlled by a strip of unsteady heat flux placed on the surface of the airfoil. Various locations pre- and post of the shock location are numerically investigated. The heat input, in this case, is very small compared to the kind needed for a simple room heater.

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Why is it important?

Shock waves degrade aerodynamic performance and thus any method which can help in controlling/suppressing these are ideal. In our specific method, we are consuming a very small amount of thermal energy to effectively control the shock.