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Force and pressure recovery characteristics at supersonic speeds of a conical spike inlet with a bypass discharging from the top or bottom of the diffuser in an axial direction
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1953 |
| Description | Force and pressure-recovery characteristics of a nacelle-type conical-spike inlet with a fixed-area bypass located in the top or bottom of the diffuser are presented for flight Mach numbers of 1.6, 1.8, and 2.0 for angles of attack from 0 degrees to 9 degrees. Top or bottom location of the bypass did not have significant effects on diffuser pressure-recovery, bypass mass-flow ratio, or drag coefficient over the range of angles of attack, flight Mach numbers, and stable engine mass-flow ratios investigated. A larger stable subcritical operating range was obtained with the bypass on the bottom at angles of attack from 3 degrees to 9 degrees at a flight Mach number of 2.0. At a flight Mach number of 2.0, the discharge of 14 percent of the critical mass flow of the inlet by means of a bypass increased the drag only one-fifth of the additive drag that would result for equivalent spillage behind an inlet normal shock without significant reductions in diffuser pressure recovery. |
| File Size | 13866234 |
| Page Count | 29 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930087574 |
| Archival Resource Key | ark:/13960/t73v3xg2t |
| Language | English |
| Publisher Date | 1953-03-23 |
| Access Restriction | Open |
| Subject Keyword | Diffusers, Subsonic Air Inlets - Nose, Annular Exits Bodies, Ducted - Nose Shape Exits, Side - Ducted Bodies 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 |
