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Performance of a supersonic ramp-type side inlet with ram-scoop throat bleed and varying fuselage boundary-layer removal : mach number range 1.5 to 2.0 / glenn a. mitchell and robert c. campbell
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1957 |
| Description | Provided sufficient throat bleed was employed, maximum pressure recoveries of 0.87 to 0.88 at Mach number 2.0 were obtained for a fuselage-mounted 14 degrees ramp inlet regardless of the amount of fuselage boundary layer ingested. The addition of inlet side fairings yielded further increases in pressure recovery to 0.90 to 0.91, decreased critical drag coefficients, and increased critical mass-flow ratios. With throat bleed, peak pressure recoveries and calculated thrust-minus-drag values were comparable at two axial positions of the scoop and were highest with the greatest amount of fuselage boundary layer ingested. |
| File Size | 14948419 |
| Page Count | 31 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930089448 |
| Archival Resource Key | ark:/13960/t79s6gs0t |
| Language | English |
| Publisher Date | 1957-01-17 |
| 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 |
