|
|
|
|
|
Yasumasa Watanabe, Alec Houpt and Sergey B. Leonov
This study considers the effect of an electric discharge on the flow structure near a 19.4° compression ramp in Mach-2 supersonic flow. The experiments were conducted in the supersonic wind tunnel SBR-50 at the University of Notre Dame. The stagnation te...
ver más
|
|
|
|
|
|
|
|
|
|
|
Tingkai Dai and Bo Zhang
Shock wave/turbulent boundary layer interaction (SBLI) is one of the most common physical phenomena in transonic wing and supersonic aircraft. In this study, the compression ramp SBLI (CR-SBLI) was simulated at a 24° corner at Mach 2.84 using the open-so...
ver más
|
|
|
|
|
|
|
|
|
|
|
Kung-Ming Chung, Kao-Chun Su and Keh-Chin Chang
A convex corner models the upper surface of a deflected flap and shock-induced boundary layer separation occurs at transonic speeds. This study uses micro-vortex generators (MVGs) for flow control. An array of MVGs (counter-rotating vane type, ramp type ...
ver más
|
|
|
|
|
|
|
|
|
|
|
Nurfathin Zahrolayali, Mohd Rashdan Saad, Azam Che Idris and Mohd Rosdzimin Abdul Rahman
Utilization of a heat source to regulate the shock wave?boundary layer interaction (SWBLI) of hypersonic inlets during throttling was computationally investigated. A plug was installed at the intake isolator?s exit, which caused throttling. The location ...
ver más
|
|
|
|
|
|
|
|
|
|
|
Andrea Ferrero
Supersonic inlets are a key component of present and future air-breathing propulsion systems for high-speed flight. The inlet design is challenging because of several phenomena that must be taken under control: shock waves, boundary layer separation and ...
ver más
|
|
|
|
|
|