TY - JOUR
T1 - Convergence rate of hypersonic similarity for steady potential flows over two-dimensional Lipschitz wedge
AU - Kuang, Jie
AU - Xiang, Wei
AU - Zhang, Yongqian
PY - 2023/4
Y1 - 2023/4
N2 - This paper is devoted to establishing the convergence rate of the hypersonic similarity for the inviscid steady irrotational Euler flow over a two-dimensional Lipschitz slender wedge in BV ∩ L1 space. The rate we established is the same as the one predicted by Newtonian-Busemann law (see (3.29) in [2, p 67] for more details) as the incoming Mach number M∞ → ∞ for a fixed hypersonic similarity parameter K. The hypersonic similarity, which is also called the Mach-number independence principle, is equivalent to the following Van Dyke’s similarity theory: For a given hypersonic similarity parameter K, when the Mach number of the flow is sufficiently large, the governing equations after the scaling are approximated by a simpler equation, that is called the hypersonic small-disturbance equation. To achieve the convergence rate, we approximate the curved boundary by piecewisely straight lines and find a new Lipschitz continuous map Ph such that the trajectory can be obtained by piecing together the Riemann solutions near the approximated boundary. Next, we derive the L1 difference estimates between the approximate solutions Uh,ν(τ)(x, ·) to the initial-boundary value problem for the scaled equations and the trajectories Ph(x, 0)(U0ν) by piecing together all the Riemann solvers. Then, by the uniqueness and the compactness of Ph and Uh,ν(τ), we can further establish the L1 estimates of order τ2 between the solutions to the initial-boundary value problem for the scaled equations and the solutions to the initial-boundary value problem for the hypersonic small-disturbance equations, if the total variations of the initial data and the tangential derivative of the boundary are sufficiently small. Based on it, we can further establish a better convergence rate by considering the hypersonic flow past a two-dimensional Lipschitz slender wing and show that for the length of the wing with the effect scale order O(τ-1), that is, the L1 convergence rate between the two solutions is of order O(τ3/2) under the assumption that the initial perturbation has compact support. © The Author(s), under exclusive licence to Springer-Verlag GmbH Germany, part of Springer Nature 2023.
AB - This paper is devoted to establishing the convergence rate of the hypersonic similarity for the inviscid steady irrotational Euler flow over a two-dimensional Lipschitz slender wedge in BV ∩ L1 space. The rate we established is the same as the one predicted by Newtonian-Busemann law (see (3.29) in [2, p 67] for more details) as the incoming Mach number M∞ → ∞ for a fixed hypersonic similarity parameter K. The hypersonic similarity, which is also called the Mach-number independence principle, is equivalent to the following Van Dyke’s similarity theory: For a given hypersonic similarity parameter K, when the Mach number of the flow is sufficiently large, the governing equations after the scaling are approximated by a simpler equation, that is called the hypersonic small-disturbance equation. To achieve the convergence rate, we approximate the curved boundary by piecewisely straight lines and find a new Lipschitz continuous map Ph such that the trajectory can be obtained by piecing together the Riemann solutions near the approximated boundary. Next, we derive the L1 difference estimates between the approximate solutions Uh,ν(τ)(x, ·) to the initial-boundary value problem for the scaled equations and the trajectories Ph(x, 0)(U0ν) by piecing together all the Riemann solvers. Then, by the uniqueness and the compactness of Ph and Uh,ν(τ), we can further establish the L1 estimates of order τ2 between the solutions to the initial-boundary value problem for the scaled equations and the solutions to the initial-boundary value problem for the hypersonic small-disturbance equations, if the total variations of the initial data and the tangential derivative of the boundary are sufficiently small. Based on it, we can further establish a better convergence rate by considering the hypersonic flow past a two-dimensional Lipschitz slender wing and show that for the length of the wing with the effect scale order O(τ-1), that is, the L1 convergence rate between the two solutions is of order O(τ3/2) under the assumption that the initial perturbation has compact support. © The Author(s), under exclusive licence to Springer-Verlag GmbH Germany, part of Springer Nature 2023.
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U2 - 10.1007/s00526-023-02449-y
DO - 10.1007/s00526-023-02449-y
M3 - RGC 21 - Publication in refereed journal
SN - 0944-2669
VL - 62
JO - Calculus of Variations and Partial Differential Equations
JF - Calculus of Variations and Partial Differential Equations
IS - 3
M1 - 106
ER -