Philosophy and Recent Developments in Aerodynamic Heating and Drag Reduction

New ideas of drag reduction and thermal protection for hypersonic vehicles is proposed based on the new technologies for shock reconstruction. In principle, a blunt vehicle flying at hypersonic speeds generates a strong bow shock wave a head of its nose, which is responsible for the high drag and aeroheating levels. There have been a number of efforts devoted towards reducing both the drag and the aeroheating by modifying the flow field ahead of the vehicle’s nose. We introduce recent development in hypersonic aerodynamic heating and drag reduction techniques. We classify this techniques in four major group. Geometrical, mass injection, energy deposition and magneto aerodynamic techniques. In this review we introduce this new techniques and investigation the philosophy and development procedure of this techniques and then we show the effects of this method to drag wave and aerodynamic heating reduction. Geometrical techniques such as structural spike and aerodisk, cavity, multi row disk (MRD) use to drag reduction. Mass injection techniques like arrays of micro jets, spike and jet, heat addition and plasma injection are very useful to aerodynamic heating reduction. Energy deposition techniques by using laser and plasma can reduce aerodynamic heating and wave drag of hypersonic flows. Magneto aerodynamic technique by addition the magneto technology in hypersonic flows can be reduce drag aerodynamic heating. The present paper is devoted to surveying these studies and illustrating the contributions of the authors in this field. The paper also raises some of the areas in the field that need further investigations.

کلیدواژه ها:

Hypersonic Flow ، Drag ، Aerodynamic Heating ، Energy ، Heat and Drag Reduction