Aerodynamic and Static-Stability Analysis of the Hypersonic Applied Research Technology (HART) Missile.

摘要

The flow about the complete Hypersonic Applied Research Technology (HART) missile is simulated for inviscid, laminar, and turbulent conditions and Mach numbers from 2 to 6. An explicit, second-order-accurate, flux-difference-splitting, algorithm is implemented and employed to solve the Navier-Stokes equations. The equations are solved using a finite-volume methodology. The aerodynamic and static-stability characteristics are investigated to determine if conventional supersonic missile configurations can be flown at Mach numbers higher than 5. The effects of nosetip blunting and boundary-layer condition are demonstrated. The structure of the flow near the fins is significantly affected by the turbulent transport of momentum in regions of blocked cross flow. Turbulence and the blockage phenomenon cause bleeding around the fin leading edges. Ultimately, this results in lower fin effectiveness and reduced static stability. The aerodynamic characteristics of the HART missile are predicted at Mach numbers beyond the experimental free-flight testing capabilities. The current predictions indicated that the pitching-moment coefficient decreases with increasing Mach number much less than previous numerical computations. The present results also suggest that the clipped-delta-fin configuration is stable beyond Mach 7.