Loading...
Please wait, while we are loading the content...
Similar Documents
Performance of a blunt-lip side inlet with ramp bleed, bypass, and a long constant-area duct ahead of the engine : mach numbers 0.66 and 1.5 to 2.1
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1956 |
| Description | Unsteady shock-induced separation of the ramp boundary layer was reduced and stabilized more effectively by external perforations than by external or internal slots. At Mach 2.0 peak total-pressure recovery was increased from 0.802 to 0.89 and stable mass-flow range was increased 185 percent over that for the solid ramp. Peak pressure recovery occurred just before instability. The 7 and one-third-diameter duct ahead of the engine reduced large total-pressure distortions but was not as successful for small distortions as obtained with throat bleed. By removing boundary-layer air the bypass nearly recovered the total-pressure loss due to the long duct. |
| File Size | 25564276 |
| Page Count | 54 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930089455 |
| Archival Resource Key | ark:/13960/t14n3x32g |
| Language | English |
| Publisher Date | 1956-12-28 |
| 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 |
