The Application of Concentric Vortex Simulation to Calculating the Aerodynamic Characteristics of Bodies of Revolution at High Angles of Attack,
FOREIGN AEROSPACE SCIENCE AND TECHNOLOGY CENTER WRIGHT-PATTERSON AFB OH
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The aerodynamic characteristic of sharp nosed bodies of revolution is calculated by using concentric vortex simulation in this paper. Based on the experimental results, an appropriate set of free integration parameters is selected and an empirical relation between initial separation angle and the Reynolds number is established. Thus, the effect of the Reynolds number is reasonably considered in the calculation. The effect of the Mach number is corrected by using Gotherts rule. The differential equations of vortex motion are solved by using the fourth order Runge Kutta method with varying step size. Three different initial step sizes are used in different integration positions in order to increase the speed of calculation. Two models F3Al6 and F3.5A7 were calculated in this paper.
- Fluid Mechanics