Abstract
The local flowfield effects of vortex generators on a supersonic axisymmetric-relaxed external compression inlet have been investigated with surface-flow visualization and pressure-sensitive paint measurements. This inlet entails a mechanically simple design for providing a high-recovery/low- distortion flowfield and low sonic-boom signature. A set of vortex generators was incorporated into the design both upstream of the terminating normal shock and downstream inside the subsonic inlet diffuser for reducing separation zones near the shock/boundary-layer interaction and reducing radial distortion at the engine face, respectively. The inlet centerbody and downstream diffuser vortex-generator regions were imaged during wind-tunnel testing internally through the inlet cowl with a camera housing attached to the cowl. Surface-flow visualization revealed separated regions along the inlet centerbody for large mass-flow rates without vortex generators. Upstream vortex generators did reduce separation in the subsonic diffuser, and a unique perspective of the flowfield produced by the downstream vortex generators was obtained. In addition, pressure distributions on the inlet centerbody, vortex generators, and struts were measured.
Original language | English (US) |
---|---|
Pages (from-to) | 1243-1257 |
Number of pages | 15 |
Journal | Journal of Propulsion and Power |
Volume | 28 |
Issue number | 6 |
DOIs | |
State | Published - 2012 |
ASJC Scopus subject areas
- Aerospace Engineering
- Fuel Technology
- Mechanical Engineering
- Space and Planetary Science