Numerical study of hypersonic turbulent flow about segmented projectiles

Abstract

The flow structure about a segmented projectile in hypersonic turbulent flow has been studied. The Reynoldsaveraged Navier-Stokes equations were solved numerically by application of the implicit monotonized scheme of second-order accuracy, the modified Newton's method, and the Christoffel-Schwarz grid-transformation technique. A strong interference effect has been found. The effect can be characterized by non-monotonous distributions of skin friction, heat flux and pressure along the second segment of the projectile. Nomenclature C f = local skin friction coefficient C p = pressure coefficient c p , c = specific heats at constant pressure and volume D = diameter of the projectile E, G = flux-vectors in curvilinear coordinate system, Eqs.(l),(2) e = total energy per unit volume, p(c^T+(u~ ~ v~)/2) H = total enthalpy per unit volume, c p T + (if-f v~)/2 /? = node size J = Jacobian of the coordinates transformation

Challenge in the aerospace university classroom

“…He tried unsuccessfully to solve the problem using the continuum approach. 141,142 Continuing his efforts, the student analyzed in depth the box schemes for systems of multi-dimensional equations of gas dynamics using the Yanenko-Shokin technique 143 of the group classification. As an alternative, the direct simulation Monte Carlo technique 123,137 has been used to study flow patterns and aerodynamic characteristics of a torus, 144 which is the best fit for a "bagel".…”

“…85 This "tough" way of learning and studying is beneficial for students allowing them to formulate new physical ideas, 85,140 to develop new numerical algorithms 86,141 and applications. 141,142 At the same time, it is a challenge for a professor as well, to be at the modern edge of science and research.…”