Three-dimensional supersonic flow over a spike-nosed body of revolution

Abstract

The unsteady, viscous, supersonic flow over a spike-nosed body of revolution is numerically investigated by solving the Navier-Stokes equations. The time-accurate computations are performed employing an implicit algorithm based on the second-order time-accurate LU-SGS scheme with the incorporation of a subiteration procedure to maintain time accuracy. The characteristics of the flow field for a Mach number of 3.0, Reynolds number of 7.87 x 10(6)/m, and angles of attack of 5 and 10 degrees are described. Self-sustained asymmetric shock wave oscillations were observed in the numerical computations for these angles of attack. The main characteristic of the flow field, as well as its influence on drag coefficient is discussed

Hypersonic Flow Field Reconfiguration and Drag Reduction of Blunt Body with Spikes and Sideward Jets

“…Comparing with the pure blunt sphere cylinders, the spikes reduce wave drag as much as 35-65%, which has been confirmed by other studies [15][16][17]. Bushnell pointed out that the effective load can be increased by 5-10% if the aerodynamic drag got discounted by as much as 1%, which is likely why so many studies have been conducted regarding spiked blunt bodies [33].…”

“…In some critical cases, the spiked blunt body changed into a resistance element [15,16]. Morgenstern showed that an asymmetric flow field in a three-dimensional simulation resulted in unsteady fluctuation during flight with attack angle, leading to axial pulsation and normal forces, which resulted in an extreme disadvantage for flight and controlling [17]. Thurman [18] and Schulein [19] achieved some positive results by changing aerodynamic characteristics utilizing a rotating spike, which required a special system to control and rotate the rod and was too complicated for practical application.…”

Three Dimensional Simulation of Supersonic Flow over Missiles of Different Shapes

“…In contrast, a numerical prediction give the same result with a short-time and an accurate computation and the computer program may be changed easily to deal with any other sort of supersonic missile [1]. Morgenstern [2] simulated the unsteady, viscous, supersonic flow over a spike-nosed body of revolution numerically by solving Navier-Stokes equations. Scalabrin et al [3] simulated the aerodynamic flow over a multi-stage rocket by using finite element method while Wilcox et al [4] presented a wind tunnel investigation of a square cross-sectional missile configuration in order to obtain force and moment measurements.…”