Computational and Experimental Study of Supersonic Nozzle Flow and Aft-Deck Interactions

Abstract

NASA has been conducting research into reducing sonic boom and changing FAA regulations to allow for supersonic commercial transport over land in the United States. This particular study looks at a plume passing through a shock generated from an aft deck on a nacelle; the aft deck is meant to represent the trailing edge of a wing. NASA Langley Research Center USM3D CFD code results are compared to the experimental data taken at the NASA Glenn Research Center 1-foot by 1-foot Supersonic Wind Tunnel. This study included examining two turbulence models along with different volume sourcing methods for grid generation. The results show that using the k-epsilon turbulence model within USM3D produced shock signatures that closely follow the experimental data at a variety of nozzle pressure ratio settings. NomenclatureNPR Nozzle Pressure Ratio GRC Glenn Research Center p static pressure, psf p ∞ freestream static pressure, psf ∆ p (p -p ∞ ), psf R Rankine SWT Supersonic Wind Tunnel x distance in the stream-wise direction, inches z distance in the waterline direction, inches * Undergraduate, AIAA Student Member.