Open AccessPerformance study of a supersonic inlet in the presence of a heat source
Author(s) -
Mohammad Reza Soltani,
Mohammad Farahani,
Javad Sepahi-Younsi
Publication year - 2011
Publication title -
scientia iranica
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.299
H-Index - 51
eISSN - 2345-3605
pISSN - 1026-3098
DOI - 10.1016/j.scient.2011.05.027
Subject(s) - inlet , mach number , mechanics , supersonic speed , drag , supersonic wind tunnel , drag coefficient , wind tunnel , materials science , drag divergence mach number , choked flow , mass flow , flow (mathematics) , meteorology , thermodynamics , physics , mechanical engineering , engineering
The flow over a supersonic inlet has been investigated experimentally and numerically at a free stream Mach number of 2 and a zero degree angle of attack. Wind tunnel tests were performed to obtain the performance parameters of the inlet and were used as a baseline and validation tools for the numerical code. A heat source was added to the flow field at a distance ahead of the inlet. The effect of heat source addition on the main performance parameters of the inlet is investigated numerically. Results show that the heat source considerably reduces drag coefficient; however, its effect on pressure recovery is not favorable. This unfavorable effect was then minimized by controlling heat source parameters, such as its location, size and shape. For the optimum condition, drag coefficient reduces considerably, inlet mass flow rate increases, but pressure recovery slightly decreases