Direct numerical simulation and analysis of a spatially evolving supersonic turbulent boundary layer at M=2.25

Abstract

A spatially developing supersonic adiabatic flat plate boundary layer flow (at M-infinity=2.25 and Re(theta)approximate to4000) is analyzed by means of direct numerical simulation. The numerical algorithm is based on a mixed weighted essentially nonoscillatory compact-difference method for the three-dimensional Navier-Stokes equations. The main objectives are to assess the validity of Morkovin's hypothesis and Reynolds analogies, and to analyze the controlling mechanisms for turbulence production, dissipation, and transport. The results show that the essential dynamics of the investigated turbulent supersonic boundary layer flow closely resembles the incompressible pattern. The Van Driest transformed mean velocity obeys the incompressible law-of-the-wall, and the mean static temperature field exhibits a quadratic dependency upon the mean velocity, as predicted by the Crocco-Busemann relation. The total temperature has been found not to be precisely uniform, and total temperature fluctuations are found to be non-negligible. Consistently, the turbulent Prandtl number is not unity, and it varies between 0.7 and 0.8 in the outer part of the boundary layer. Nonetheless, a modified strong Reynolds analogy is still verified. In agreement with the low Mach number results, the streamwise velocity component and the temperature are only weakly anti-correlated. The turbulent kinetic energy budget also shows similarities with the incompressible case provided all terms of the equation are properly scaled; indeed, the leading compressibility contributions are negligible throughout the boundary layer. (C) 2004 American Institute of Physics

DNS of a spatially evolving hypersonic turbulent boundary layer at Mach 8

“…However, Liang et al [14] proposed that the SRA is valid for T w /T ∞ =10.03 and Ma ∞ =8 in whole boundary layer. Similar results have been reported for Mach 2.25 [3] and 5 [9].…”

“…(9) R , but also indicate that the correlation of u″ and v″ is not considered strong, as well as weak correlation between v″ and T″. Such results are similar [3] for the lower Mach number case. When y + <50, the predicted results by eqs.…”

“…(8) and (9) Pr  is a measure of the ratio of the turbulent kinematic viscosity over the turbulent mass diffusivity. Morkovin's hypothesis also implies that Pr t and Pr  approximates 1 [3]. Figure 10 depicts the distributions of the turbulent Prandtl numbers for the case of M8T1.…”

“…Furthermore, the DNS results of the spatial simulations are studied for the compressible boundary layer with Ma ∞ =2.25 and Re ∞ =635000 over the flat-plate boundary layer [3][4][5]. The results show that the essential dynamics of the turbulent boundary layer closely resemble the incompressible case.…”

“…Furthermore, the position of peak value of P is at about y * ≈12. The results [3,5,9,12,14] are taken from the adiabatic or near to recovery temperature wall case, which does not cause significant compressibility. Thus, we believe that the present difference is caused by compressi- bility effects.…”