Abstract
A numerical simulation of the flow inside a diffusing S-duct inlet is conducted. The primary discussion herein focuses on flow analysis and development of secondary flow in the S-duct diffuser inlet. Full three-dimensional Navier-Stokes equations are solved and SST turbulence model is employed. Numerical results, including surface static pressure, total pressure recovery at exit, are compared with experiment. And fairly good agreement is apparent. Total performance, such as average total pressure recovery and distortion, is agreed well with the experiment. Shock waves in outer flow, pressure recovery and distortion at the exit are also discussed.
Highlights
S-duct inlet has been widely used for military and commercial aircraft, such as F-16, F-18 and Boeing 727
Increasing cross-sectional area can lead to adverse pressure gradients
Predicted surface static pressure and pressure recovery at exit are compared with experiment to insure accuracy of the computation
Summary
S-duct inlet has been widely used for military and commercial aircraft, such as F-16, F-18 and Boeing 727. Inlet should decelerate the flow to the desired velocity while maintaining high total pressure recovery and flow uniformity. In S-duct inlet two bends give rise to streamline curvature. The streamline curvature results in cross-stream pressure gradients which can produce significant secondary flows. Increasing cross-sectional area can lead to adverse pressure gradients. All of mentioned above increase risk of unacceptable inlet performance. Understanding flow in S-duct inlet is very important in inlet design process.( S.R.Wellborn, B.A.Reichert, T.H.Okiishi,1992; B.A.Reichert, B.J.Wendt1993; G.J. Harloff, B.A. Reichert, S.R. Wellborn,1992)
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