Velocimetry Measurements of Unstart in an Inlet-Isolator Model in Mach 5 Flow

Wagner J. L., Yüceil K. B., CLEMENS N. T.

AIAA JOURNAL, vol.48, no.9, pp.1875-1888, 2010 (SCI-Expanded) identifier identifier

  • Publication Type: Article / Article
  • Volume: 48 Issue: 9
  • Publication Date: 2010
  • Doi Number: 10.2514/1.j050037
  • Journal Name: AIAA JOURNAL
  • Journal Indexes: Science Citation Index Expanded (SCI-EXPANDED), Scopus
  • Page Numbers: pp.1875-1888
  • Istanbul Technical University Affiliated: Yes


The dynamics of unstart in a floor-mounted inlet-isolator model in a Mach 5 flow are investigated experimentally using particle image velocimetry and fast-response wall pressure measurements. The inlet compression is obtained with a 6-deg ramp and the isolator is a rectangular straight duct that is 25.4 nun high by 50.8 min wide by 242.3 nun long. Unstart is initiated from the scramjet mode (fully supersonic in the isolator) by deflecting a motorized flap at the downstream end of the isolator. With the flap fully down, the particle image velocimetry data of the started flow capture the characteristics of the isolator boundary layers and the initial inlet reflected shock system. During unstart. the unstart shock system propagates upstream through the inlet-isolator. The particle image velocimetry (lath reveal a complex, three-dimensional flow structure that is strongly dependent on viscous mechanisms. Particularly., the unstart shock system propagates upstream and induces significant boundary-layer separation. Side-view particle image velocimetry data show that the locations of strongest separation during unstart correlate with the impingement locations of the initial inlet shock as it reflects down the isolator. For example. in the middle of [install, the unstart shock system is associated with massive separation of the ceiling boundary layer that begins where the first inlet shock reflection impinges on the ceiling. The observation that separation increases at the inlet shock reflection impingement locations is likely due to the fact that the boundary layers in these locations are subject to larger adverse pressure gradients. thus making them more susceptible to separation. During the unstart princess, large regions of separated flow form near the floor and ceiling with reverse flow velocities up to about 0.4U(infinity). These regions of separated. subsonic flow appear to extend to the isolator exit, creating a path by which the isolator exit boundary condition can be communicated upstream. Plan-view particle image velocimetry data show the unstart process begins with separation of the isolator sidewall boundary layers. Overall, the unstart flow structure is highly three-dimensional.