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Space shuttle maneuvering engine reusable thrust chamber program. task 11: low epsilon stability test plan
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Pauckert, R. P. |
| Copyright Year | 1974 |
| Description | The performance and heat transfer characteristics of a doublet element type injector for the space shuttle orbiter maneuvering engine thrust chamber were investigated. Ths stability characteristics were evaluated over a range of chamber pressures and mixture ratios. The specific objectives of the test were: (1) to determine whether stability has been influenced by injection of boundary layer coolant across the cavity entrance, (2) if the injector is stable, to determine the minimum cavity area required to maintain stability, and (3) if the injector is unstable, to determine the effects of entrance geometry and increased area on stability. |
| File Size | 286730 |
| Page Count | 12 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19740023163 |
| Archival Resource Key | ark:/13960/t3dz5179s |
| Language | English |
| Publisher Date | 1974-01-01 |
| Access Restriction | Open |
| Subject Keyword | Propulsion Systems Flow Stability Air Flow Performance Tests Space Shuttles Cooling Systems Flow Characteristics Combustion Chambers Rocket Engine Design Spacecraft Propulsion Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
