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Large Eddy Simulation of Supersonic Compression Corner Using ENO Scheme

A Large Eddy Simulation of a 250 compression corner at M 2.88 and 
Red 2 x 104 is performed using an Essentially Non Oscillatory (ENO) 
scheme. The Favre filtered compressible Navier-Stokes equations are solved 
using a Monotone Integrated Large Eddy Simulation (MILES) technique 
on an unstructured grid of tetrahedral cells. The mean flow variables and 
turbulent shear stress at the incoming flow are in good agreement with 
experiment and DNS. The separation length scaled by the characteristic 
scale [27, 31] shows agreement with the experiment. No pronounced pres- 
sure plateau is observed compared with experiment at higher Reynolds 
number. 
2. Introduction 
Supersonic flow over a compression corner is a classic problem embody- 
ing all the difficulties of viscous/inviscid interactions, compressibility and 
turbulence. A full understanding of this configuration is important for ef- 
ficient aerodynamic and propulsion design. An extensive effort [1, 3, 4, 6, 
7, 8, 10, 11, 15, 16, 17, 18, 20, 21, 22, 24, 25, 26, 27, 29, 30, 31, 32] 
been focused on the study of this flow. However, traditional RANS meth-

ods have not accurately predicted the heat transfer and skin friction coeffi- 
cient[3, 4, 10, 18, 29, 30] in cases with large flow separation. In addition, the 
scaled seperation length proposed in [27, 31] shows a significant deviation 
from the experimental range in Fig. I. A Very Large Eddy Simulation by 
Hunt [11] for a 240 Mach 2.8 compression corner at Red = 106 revealed 
that the size of the separation bubble correlates strongly with the shock 
wave position. A DNS of 180 Mach 3 compression corner at Reo = 1685 
implemented by Adams [I] indicated the effect of compressibility on the tur- 
bulence structure in the interaction area. Rizzetta et al. [16, 17] performed 
a DNS and LES of 180 compression corner and made full comparison with 
DNS results by Adams [1]. 
This paper implements an ENO scheme for a 250 compression corner at 
Mach 2.88 and Re5 = 2 x 104 to assess the capability of LES to accurately 
predict the turbulence characteristics.