Numerical Analysis of Hypersonic Flow Past Blunt Bodies with Aerospikes

Abstract

Aerodynamic drag, as a result of the high surface pressure generated because of the formation of a bow shock in front of a blunt nose cone of a hypersonic vehicle, is a serious problem. An aerospike can be attached to the stagnation point of the blunt nose cone to achieve a large reduction in drag and heat load at very high speeds in supersonic or hypersonic range. Aerospike replaces the strong detached shock wave with a system of weaker oblique shock waves, and a recirculation zone is formed between the shock and the body. Aerodynamic drag reduction on supersonic and hypersonic vehicles helps in reaching the desired range or altitude, allows economizing the fuel usage, simplifies the propulsion system requirements, and maximizes the ratio of payload to takeoff gross weight. In the present study, the flow around a blunted nose cone fitted with an aerospike is numerically simulated. An analysis is performed at a high Mach number () and different length-to-diameter ratios (, 2) at different angles of attack (0, 2, 5, and 8 deg). Numerical calculations agree well with the corresponding experimental results.