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Further shock tunnel studies of scramjet phenomena
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Stalker, R. J. Paull, A. Morgan, R. G. Morris, N. A. |
| Copyright Year | 1986 |
| Description | Scramjet phenomena were studied using the shock tunnel T3 at the Australian National University. Simple two dimensional models were used with a combination of wall and central injectors. Silane as an additive to hydrogen fuel was studied over a range of temperatures and pressures to evaluate its effect as an ignition aid. The film cooling effect of surface injected hydrogen was measured over a wide range of equivalence. Heat transfer measurements without injection were repeated to confirm previous indications of heating rates lower than simple flat plate predictions for laminar boundary layers in equilibrium flow. The previous results were reproduced and the discrepancies are discussed in terms of the model geometry and departures of the flow from equilibrium. In the thrust producing mode, attempts were made to increase specific impulse with wall injection. Some preliminary tests were also performed on shock induced ignition, to investigate the possibility in flight of injecting fuel upstream of the combustion chamber, where it could mix but not burn. |
| File Size | 3454540 |
| Page Count | 110 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19870003109 |
| Archival Resource Key | ark:/13960/t8qc4wz61 |
| Language | English |
| Publisher Date | 1986-05-12 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Pressure Sensors Silanes Gas Dynamics Supersonic Combustion Ramjet Engines Two Dimensional Models Nozzle Geometry Combustion Physics Stagnation Pressure Pressure Measurement Film Cooling Heat Transfer Mach Number Shock Tunnels Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
