Preliminary Design of a 2D Supersonic Inlet to Maximize Total Pressure Recovery

Show full item record

Please use this identifier to cite or link to this item: http://hdl.handle.net/1853/25446

Title: Preliminary Design of a 2D Supersonic Inlet to Maximize Total Pressure Recovery
Author: Ran, Hongjun ; Mavris, Dimitri N.
Abstract: This paper provides a method of preliminary design for a two-dimensional, mixed compression, two-ramp supersonic inlet to maximize total pressure recovery and match the mass flow demand of the engine. For an on-design condition, the total pressure recovery is maximized according to the optimization criterion, and the dimensions of the inlet in terms of ratios to the engine face diameter are calculated. The optimization criterion is defined such that in a system of (n-1) oblique shocks and one normal shock in two dimensions, the maximum shock pressure recovery is obtained when the shocks are of equal strength. This paper also provides a method to estimate the total pressure recovery for an off-design condition for the specified inlet configuration. For an off-design condition, conservative estimation of the total pressure recovery is given so that performance of the engine at the off-design condition can be estimated. To match the mass flow demand of the engine, the second ramp angle is adjusted and the open/close schedule of a bypass door is determined. The effects of boundary layer are not considered for the supersonic part of the inlet, however friction and expansion losses are considered for the subsonic diffuser.
Description: Presented at the AIAA 5th Aviation, Technology, Integration, and Operations Conference (ATIO), 26 - 28 September 2005, Arlington, Virginia.
Type: Paper
URI: http://hdl.handle.net/1853/25446
Date: 2005-09
Contributor: Georgia Institute of Technology. Aerospace Systems Design Laboratory
Relation: ASDL; AIAA 2005-7357
Publisher: Georgia Institute of Technology
Subject: Aircraft engines
Engine design
Pressure recovery
Supersonic inlets
Preliminary designs
Oblique shock waves
Subsonic diffusers
Normal shock waves

All materials in SMARTech are protected under U.S. Copyright Law and all rights are reserved, unless otherwise specifically indicated on or in the materials.

Files in this item

Files Size Format View
Ran_2005_1.pdf 317.3Kb PDF View/ Open

This item appears in the following Collection(s)

Show full item record