Laminar boundary layer stability calculation for contoured Mach 6 nozzle

• Published in: Thermophysics and aeromechanics Vol. 27; no. 1; pp. 35 - 44
• Main Authors: Morozov, S. O., Shiplyuk, A. N.
• Format: Journal Article
• Language: English
• Published: Novosibirsk Kutateladze Institute of Thermophysics SB RAS 2020; Springer Nature B.V
• Subjects: Boundary layer stability; Computational fluid dynamics; Fluid flow; Hypersonic nozzles; Laminar boundary layer; Mach number; Mathematical analysis; Physics; Physics and Astronomy; Reynolds number; Thermodynamics; Vortices; Wind tunnels; Goertler vortices; hypersonic nozzle; linear stability theory; boundary layer; laminar-turbulent transition
• ISSN: 0869-8643; 1531-8699
• DOI: 10.1134/S0869864320010035

Stability of the laminar boundary layer on the surface of a hypersonic nozzle for the Mach number M = 6 of the Transit-M wind tunnel is calculated. The laminar boundary-layer profiles are obtained by solving the Navier-Stokes equations numerically within the framework of the Ansys Fluent software.
N
-factors of the Goertler vortices and of the first and second Mack modes are obtained in the approximation of the linear stability theory. It is demonstrated that the Goertler vortices are the most unstable disturbances for the nozzle under consideration. Empirical dependences of the local Reynolds number of the laminar-turbulent transition on the
N
-factor and unit Reynolds number are determined.