Gregory A. Blaisdell

Learn More
This paper presents the results of using high-order compact schemes with a high-order filter on multi-block domains. The Linearized Euler Equations (LEE) are solved on a uniform mesh for benchmark problems in one and two dimensions. Also a two dimensional mixing layer is solved by using LargeEddy Simulation (LES). Three different boundary schemes are(More)
The performance of two popular turbulence models, the Spalart-Allmaras model and Menter’s SST model, and one relatively new model, Olsen & Coakley’s Lag model, are evaluated using the OVERFLOW code. Turbulent shock-boundary layer interaction predictions are evaluated with three different experimental datasets: a series of 2D compression ramps at Mach 2.87,(More)
The consistency of second-order closure models with results from hydrodynamic stability theory is analyzed for the simpli ed case of homogeneous turbulence. In a recent study, Speziale, Gatski and MacGiolla Mhuiris [Phys. Fluids A 2, 1678, 1990] showed that secondorder closures are capable of yielding results that are consistent with hydrodynamic stability(More)
Computational aeroacoustics (CAA) has emerged as a tool to complement theoretical and experimental approaches for robust and accurate prediction of sound levels from aircraft airframes and engines. CAA, unlike computational fluid dynamics (CFD), involves the accurate prediction of small-amplitude acoustic fluctuations and their correct propagation to the(More)
Isotropic compressible turbulence subjected to rapid isotropic compression is studied using inviscid rapid distortion theory ~RDT! and direct numerical simulation. An exact solution to the rapid distortion problem is given. Comparisons are made between the simulation results and the RDT solution, as well as previously studied limiting cases of the RDT(More)
The capability of the OVERFLOW code to accurately compute high-speed turbulent boundary layers and turbulent shock-boundary layer interactions is being evaluated. Configurations being investigated include a Mach 2.87 flat plate to compare experimental velocity profiles and boundary layer growth, a Mach 6 flat plate to compare experimental surface heat(More)
Direct numerical simulations are performed for the elliptic streamline ow which is a homogeneous turbulent ow that combines the e ects of solid body rotation and strain Simulations are run over a range of parameters in order to determine the e ect of changing rotation and strain separately For early times the nonlinear cascade is suppressed but then is re(More)