Loading...
Please wait, while we are loading the content...
Similar Documents
An experimental and analytical investigation of axisymmetric diffusers. [finite difference computer program
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Povinelli, L. A. |
| Copyright Year | 1975 |
| Description | A finite difference computer program for turbulent compressible flow was used to establish the performance of several diffuser shapes for experimental testing. The diffusers were designed to have a linear change in Mach number, a linear change in pressure, or a curvature fitted by a quadratic equation. Testing was performed with M = 0.1 to 0.9 with and without boundary layer bleed. Above M = 0.6, data were obtained with a normal shock upstream of the diffuser entrance. Peak static pressure recovery occurred with a diffuser inlet M0.75. The quadratic diffuser yielded the highest total pressure recovery. |
| File Size | 3512849 |
| Page Count | 17 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19750022933 |
| Archival Resource Key | ark:/13960/t53f9j469 |
| Language | English |
| Publisher Date | 1975-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Turbulent Flow Pressure Recovery Finite Difference Theory Performance Prediction Supersonic Diffusers Compressible Flow Computer Programs Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
