A Static Investigation of Fixed-Geometry Nozzles Using Fluidic Injection for Throat Area Control

摘要

A sub-scale, static-thrust nozzle test was conducted under a cooperative independent research and development effort by Lockheed Martin Tactical Aircraft Systems (LMTAS) and Pratt & Whitney (P&W) to validate performance of a promising aerodynamically-controlled nozzle concept. Testing focused on varying effective throat area of fixed-geometry nozzles by injecting secondary air at the nozzle throat. All nozzles were axisymmetric and possessed a forward-facing injector. Injectors designed for two secondary pressure ratios and three different injection schemes (slot, dual slot, and multi-hole injection) were compared. An evaluation of asymmetric injection was also made. These results may allow LMTAS and P&W to develop simple, low-cost exhaust systems that reduce aircraft weight and improve signature and reliability.