TY - GEN
T1 - The influence of boundary layers on supersonic inlet unstart
AU - Do, H.
AU - Im, S.
AU - Mungal, M. G.
AU - Cappelli, M. A.
N1 - Funding Information:
This work is sponsored by the Department of Energy sponsored Predictive Science Academic Alliance Program (PSAAP) at Stanford University.
PY - 2011
Y1 - 2011
N2 - A transverse air jet injected into a Mach 5 model inlet flow generated by an in-draft supersonic wind tunnel, is used to induce inlet unstart. Planar Laser Rayleigh Scattering (PLRS) from condensed CO2 particles in the tunnel flow is used to visualize the unsteady flow during unstart. Simultaneously, pressure traces along the wind tunnel are recorded with high speed pressure sensors attached to the bottom wall of the wind tunnel. A series of time synchronized PLRS images reveals that a shock system, followed by flow separation, originating from the jet injection nozzle propagates upstream. The flow then unstarts upon the arrival of the shock at the inlet. Studies conducted using three different inlet model geometries indicate that the presence of turbulent wall boundary layers strongly affect the unstart dynamics. It is found that relatively thick turbulent boundary layers result in faster inlet unstart, when compared to thin, laminar boundary layers.
AB - A transverse air jet injected into a Mach 5 model inlet flow generated by an in-draft supersonic wind tunnel, is used to induce inlet unstart. Planar Laser Rayleigh Scattering (PLRS) from condensed CO2 particles in the tunnel flow is used to visualize the unsteady flow during unstart. Simultaneously, pressure traces along the wind tunnel are recorded with high speed pressure sensors attached to the bottom wall of the wind tunnel. A series of time synchronized PLRS images reveals that a shock system, followed by flow separation, originating from the jet injection nozzle propagates upstream. The flow then unstarts upon the arrival of the shock at the inlet. Studies conducted using three different inlet model geometries indicate that the presence of turbulent wall boundary layers strongly affect the unstart dynamics. It is found that relatively thick turbulent boundary layers result in faster inlet unstart, when compared to thin, laminar boundary layers.
UR - http://www.scopus.com/inward/record.url?scp=84881286660&partnerID=8YFLogxK
U2 - 10.2514/6.2011-2349
DO - 10.2514/6.2011-2349
M3 - Conference contribution
AN - SCOPUS:84881286660
SN - 9781600869426
T3 - 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011
BT - 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011
T2 - 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011
Y2 - 11 April 2011 through 14 April 2011
ER -