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Performance and surge limits of a tf30-p-3 turbofan engine/axisymmetric mixed-compression inlet propulsion system at mach 2.5
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Wasserbauer, J. F. Shaw, R. J. Neumann, H. E. |
| Copyright Year | 1985 |
| Description | Steady-state performance and inlet-engine compatibility were investigated with a low-bleed inlet. The inlet had minimum internal contraction, consistent with high total pressure recovery and low cowl drag. The inlet-engine combination displayed good performance with only about 2% of inlet performance bleed. The inlet-engine combination had 5.58 deg angle-of-attack capability with 6% bleed. |
| File Size | 5538013 |
| Page Count | 21 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19850016950 |
| Archival Resource Key | ark:/13960/t5k982m0g |
| Language | English |
| Publisher Date | 1985-05-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Aerodynamic Configurations Propulsion System Performance Pressure Reduction Turbofan Engines Inlet Airframe Configurations Angle of Attack Intake Systems Flow Geometry 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 |
