Abstract
This work presents three-dimensional, hypersonic flow computations for a waverider-based hypersonic vehicle with finlets. The waverider geometry, as composed of an airframe and a reflexed trailing-edge, is derived from a perturbed hypersonic flow past a cone with combined transverse and small longitudinal curvature. The flowfield simulations associated with the design and off-design flight conditions are performed by solving the three-dimensional compressible Navier-Stokes equations that are incorporated with an implicit upwind-biased finite volume algorithm. Also, the lift, drag, skin friction, lift-to-drag ratio, and static margin are calculated. In the on-design conditions ( M ∞ = 4.0), the inviscid and viscous numerical results correlate well with the estimates of the hypersonic small-disturbance theory. In addition, the influence on aerodynamic performance and stability of adding finlets is discussed here. Furthermore, the variations of aerodynamic performance caused by altering the angle-of-attack from −10 to +10 ° are investigated.
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