Loading...
Please wait, while we are loading the content...
Similar Documents
Enhanced performance of streamline-traced external-compression supersonic inlets (Document No: 20150021040)
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Slater, John W. |
| Copyright Year | 2015 |
| Description | A computational design study was conducted to enhance the aerodynamic performance of streamline-traced, external-compression inlets for Mach 1.6. Compared to traditional external-compression, two-dimensional and axisymmetric inlets, streamline-traced inlets promise reduced cowl wave drag and sonic boom, but at the expense of reduced total pressure recovery and increased total pressure distortion. The current study explored a new parent flowfield for the streamline tracing and several variations of inlet design factors, including the axial displacement and angle of the subsonic cowl lip, the vertical placement of the engine axis, and the use of porous bleed in the subsonic diffuser. The performance was enhanced over that of an earlier streamline-traced inlet such as to increase the total pressure recovery and reduce total pressure distortion.|||||||||||| |
| File Size | 1286193 |
| Page Count | 10 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20150021040 |
| Archival Resource Key | ark:/13960/t18m29s11 |
| Language | English |
| Publisher Date | 2015-10-25 |
| Access Restriction | Open |
| Subject Keyword | Performance Supersonic Inlets Engine Design Supersonic Speed Computational Fluid Dynamics Pressure Recovery Engine Inlets Flow Distribution Supersonic Inlets Aircraft Design Streamlining Aerodynamic Characteristics Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
