Loading...
Please wait, while we are loading the content...
Altitude performance characteristics of tail-pipe burner with convergingconical burner section on j47 turbojet engine
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1950 |
| Description | An investigation of turbojet-engine thrust augmentation by means of tail-pipe burning was conducted in the NACA Lewis altitude wind tunnel. Performance data were obtained with a tail-pipe burner having a converging conical burner section installed on an axial-flow-compressor type turbojet engine over a range of simulated flight conditions and tail-pipe fuel-air ratios with a fixed-area exhaust nozzle. A maximum tail-pipe combustion efficiency of 0.86 was obtained at an altitude of 15,000 feet and a flight Mach number of 0.23. Tail-pipe burner operation was possible up to an altitude of 45,000 feet at a flight Mach number of 0.23. |
| File Size | 23617923 |
| Page Count | 40 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930086235 |
| Archival Resource Key | ark:/13960/t3pw0ts01 |
| Language | English |
| Publisher Date | 1950-12-19 |
| Access Restriction | Open |
| Subject Keyword | 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 |
