Abstract
Drag force control via energy deposition in an oncoming flow is a wide area of interest in aerospace sciences. Recently, investigations on the effect of combining energy sources have been conducted. The possibility of coupling microwave (MW) discharges or MW and laser energy deposition is discussed. In the present work, the flow details accompanying the interaction of a combined energy release and an aerodynamic body in a supersonic flow are considered numerically on the base of the Euler equations. Comparison with non-combined energy deposition is analyzed. The effect of introducing the internal part to the energy release on the drag force reduction is examined. The flows for blunt cylinder, hemisphere-cylinder and pointed body are considered for a wide class of the combined energy source characteristics. Freestream Mach number is varied from 1.89 to 3.45. Complicated unsteady vortex structures caused by the Richtmyer–Meshkov instabilities are shown to be the reason for the reduction in drag. The unsteady double vortex mechanism of the frontal drag force reduction and mechanism of the constantly acting vortices at the steady flow are described. Suppression of shear layer instability and large scaled flow pulsations as the result of the combined energy release effect is established. Complex conservative difference schemes are used in the simulations.
Highlights
The problem of unsteady interaction of a space distributed energy source dislocated in an oncoming supersonic flow with a shock layer was initiated in [1] on the example of the flow past a sphere.Energy source was shown to produce a significant effect causing total flow reconstruction
It is obtained that the vortex flow generated at the first stage of the interaction causes decreasing in the frontal drag force
The double vortex mechanism of the frontal drag force reduction is examined for unsteady flow past the blunt bodies
Summary
The problem of unsteady interaction of a space distributed energy source dislocated in an oncoming supersonic flow with a shock layer was initiated in [1] on the example of the flow past a sphere. Energy source was shown to produce a significant effect causing total flow reconstruction This phenomenon has been considered for the purpose of flow control via changing characteristics of an aerodynamic body (see survey in [2]). In [3], the effect of a heated rarefied channel on a supersonic flow past a blunt cylinder is examined. The interaction of a combined energy release with a supersonic flow past blunt bodies (cylinder and hemisphere-cylinder) and a pointed body is considered numerically using the. The double vortex mechanism of the frontal drag force reduction is examined for unsteady flow past the blunt bodies. The mechanism of the frontal drag force reduction connected with the constantly acting vortices is examined for the steady flow past the pointed body. Quantitative results on drag reduction for the considered simplest shapes of aerodynamic bodies are presented
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
