The present study investigates the behavior of first-mode instability waves on a 7 deg half-angle sharp cone model at zero angle of attack in Mach 3 supersonic flow, both numerically and experimentally. The primary purpose of this study is to obtain more insight of the laminar–turbulent boundary-layer transition in supersonic flow. Linear stability theory is applied on a simulated laminar mean flow to predict the property of the instability waves, such as frequency content, spatial amplification rate, and maximum amplified wave angle. Afterward, instability experiments are performed using piezoelectric pressure sensor (PCB) sensors and constant temperature anemometry on the cone model. The PCB sensors are surface mounted to capture the pressure fluctuations along the cone model, whereas the hot-wire probe of the constant temperature anemometry is traversed through the boundary layer of the cone flow at different axial stations. The instability waves are observed with both instruments. They are quantitatively characterized and compared with the numerical calculation, and good agreement is achieved. Eventually, the critical -factor is also estimated for the sharp cone in present tunnel.
Investigation of Instability Waves in a Mach 3 Laminar Boundary Layer
AIAA Journal ; 53 , 12 ; 3712-3725
2015-12-01
Article (Journal)
Electronic Resource
English
Investigation of Instability Waves in a Mach 3 Laminar Boundary Layer
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