Abstract
Second-order differential equations of the hyperbolic type are derived for describing the local law of shock wave propagation. The shock waves are assumed to be two-dimensional unsteady in a stationary gas flow and three-dimensional steady in a supersonic flow. The behavior of the characteristics of these equations is investigated as a function of the governing flow parameters and their relative position with respect to the typical bicharacteristics of the characteristic cone behind the shock is analyzed.
This is a preview of subscription content, log in via an institution to check access.
Similar content being viewed by others
References
L. D. Landau, “Shock waves at large distances from their place of formation,”Prikl. Mat. Mekh.,9, 286 (1945).
L. V. Ovsyannikov,Lectures on the Fundamentals of Gas Dynamics [in Russian], Nauka, Moscow (1981).
G. B. Whitham,Linear and Nonlinear Waves, Wiley, New York (1974).
V. V. Lunyov, “Three-dimensional theory of the body burn equation in a high-temperature gas flow,”Izv. Akad. Nauk SSSR, Mekh. Zhidk. Gaza, No. 1, 143 (1987).
V. V. Lunyov,Hypersonic Aerodynamics [in Russian], Mashinostroenie, Moscow (1975).
Additional information
Moscow. Translated from Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, No. 3, pp. 159–165, May–June, 2000.
Rights and permissions
About this article
Cite this article
Lunyov, V.V. Equation of a shock wave front. Fluid Dyn 35, 443–448 (2000). https://doi.org/10.1007/BF02697758
Received:
Issue Date:
DOI: https://doi.org/10.1007/BF02697758