Abstract
ABSTRACT This work presents a numerical analysis of the gas dynamic problem of localized and steady energy addition to uniform high-speed airflows. Firstly, the general effects caused by a localized energy deposition on the flow were investigated, then an extensive parametric analysis concerning the effects of energy deposition rate and dispersion for different free stream flow speeds was performed. As a general result, localized and steady energy deposition generates compression waves and constant property flow stream tube downstream to the source. The parametric analysis results have shown that either increasing the rate or decreasing dispersion in the orthogonal direction to the flow of the deposited energy has the effect of enhancing property flow changes, which is even more pronounced for lower flow speeds. In contrast, energy dispersion in the flow direction has presented very little effect on the flow changes. The results of this numerical analysis should be very helpful in studies of energy addition applications in hypersonic.
Highlights
The need of aerospace vehicles for high speeds discloses a series of aerodynamics problems, such as large pressure drag forces and strong shock waves
General characteristics of the flow with localized steady energy addition In order to identify the key changes of the properties of a uniform flow caused by the addition of energy to a small region in space, the physical domain shown in Fig. 1 is used to perform numerical calculations
This work has shown the effects on the flow structure of a localized and steady energy addition to uniform supersonic airflows, based only on thermodynamics and gas dynamics standpoints
Summary
The need of aerospace vehicles for high speeds discloses a series of aerodynamics problems, such as large pressure drag forces and strong shock waves. For a blunt body at supersonic speeds, a physical spike placed at its nose modifies the structure of the strong shock wave, which can reduce wave drag in an effective way, this structure requires an undesirable additional cooling system (Riggins et al, 1999, Riggins and Nelson, 1999, Knight, 2003) Another way to control high speed flows, which has been considered for the reduction of aerodynamic drag of aerospace vehicles, corresponds to energy deposition in a small region of the airflow upstream to the vehicle. Deposition of energy to airflows has been experimentally accomplished by several different means, such as plasma arcs, laser pulse, microwave, electron beam, glow discharges, and so on (Oliveira, 2008c)
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