Craig A. Hunter

TL;DR: A detailed experimental, theoretical, and computational study of separated nozzle flows has been conducted as discussed by the authors, and the results indicate that off-design overexpanded nozzle flow was dominated by shock induced boundary layer separation, which was divided into two distinct flow regimes; three-dimensional separation with partial reattachment, and fully detached 2D separation.

TL;DR: In this article, an experimental investigation of the NASA Common Research Model was conducted in the NASA Langley National Transonic Facility and NASA Ames 11-foot Transonic Wind Tunnel Facility for use in the Drag Prediction Workshop.

TL;DR: A detailed experimental study of separated nozzle flows has been conducted at the NASA Langley Research Center 16-Foot Transonic Tunnel Complex as discussed by the authors, where force, moment, and pressure measurements were made and schlieren flow visualization was obtained for a subscale, nonaxisymmetric, two-dimensional, convergent-divergent nozzle.

TL;DR: In this article, the Jet3D noise prediction method was applied to heated jets with complex three-dimensional flow fields and installation effects, and the results were made for four separate flow bypass ratio five nozzle configurations tested in the NASA Langley Jet Noise Laboratory.

TL;DR: In this paper, a computational assessment has been undertaken to investigate model support system interference effects on the Common Research Model and the results from this investigation confirm that the addition of the support system to the computational cases does shift the pitching moment in the direction of the experimental results.