Numerical Study of an Air Intake of a Cruise Missile in Subsonic Mach Regime
Author(s):
S Pani, K V Muralidharan, SK Maharana
Keywords:
Aerodynamic interface plane, , Distortions Specific fuel consumption, Total pressure recovery
Abstract
Cruise missiles are low-altitude, fast-moving guided bombs that fly parallel to the ground. Due to the need for a low specific fuel consumption (SFC) to aid in travelling greater distances, a turbofan engine is employed to propel this type of missile. Because the power plant is an air breathing engine and the route is essentially terrain hugging, the air entrance to the engine must be properly let in. Inlets are crucial to the overall functioning of a jet engine and have a substantial impact on thrust output. As the plane speeds up, the inlet duct design becomes increasingly critical. The engine thrust would be great only if the inlet duct provided the required airflow at the maximum possible pressure. The work presented here is a study and design of an air intake for a conventional cruise missile in this direction. The goal of this research is to find the overall pressure recovery coefficient at the aerodynamic interface plane (AIP) by numerically simulating airflow via the air intake. Total pressure recovery has been determined quantitatively at different positions (0o to 360o) of AIP. The intensity of circumferential and radial distortions, as well as total pressure recovery (PR) coefficients for AIP, were then estimated. The maximum PR that may be achieved is 0.9. The flow was optimized using a genetic algorithm, with the corrected mass flow serving as the fitness function.
Article Details
Unique Paper ID: 155260

Publication Volume & Issue: Volume 9, Issue 1

Page(s): 381 - 388
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