Abstract
Two-dimensional, supersonic flow field computation with by-pass holes has been
conducted using Euler equation. An algorithm based on finite difference
McCormack's technique is used to solve the subsonic-supersonic flow problem with
and without by-passing. Trials on by-pass locations were also made. Operation
without bypass shows the movement of the normal shock wave upstream which
refers to an off-design operating regime. At a distance of 1.271 m measured from the
cowl lip, the region of normal shock wave was localized near the throat which
approximately represents the on-design perform 0ance condition (cells 8-9). When
the flow is bypassed from the rear passages, the normal shock wave is sucked inside
the flow passage save poor performance. Results show that by-passing provides a
fast reaction to maintain a steady performance which meets the requirements of ondesign
operation. The Mach number variation corresponding to each case is
presented. Results show that the tendency to unity Mach number near the cowl lip
sector can be achieved using by-pass expelled. The influence of by-pass on the total
pressure recovery and relative pressure is also discussed.
conducted using Euler equation. An algorithm based on finite difference
McCormack's technique is used to solve the subsonic-supersonic flow problem with
and without by-passing. Trials on by-pass locations were also made. Operation
without bypass shows the movement of the normal shock wave upstream which
refers to an off-design operating regime. At a distance of 1.271 m measured from the
cowl lip, the region of normal shock wave was localized near the throat which
approximately represents the on-design perform 0ance condition (cells 8-9). When
the flow is bypassed from the rear passages, the normal shock wave is sucked inside
the flow passage save poor performance. Results show that by-passing provides a
fast reaction to maintain a steady performance which meets the requirements of ondesign
operation. The Mach number variation corresponding to each case is
presented. Results show that the tendency to unity Mach number near the cowl lip
sector can be achieved using by-pass expelled. The influence of by-pass on the total
pressure recovery and relative pressure is also discussed.
Keywords
Air intake
Bypass
CFD
McCormack’s technique
Pressure Recovery
Shock wave.