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Ram-recovery characteristics of naca submerged inlets at high subsonic speeds
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1948 |
| Description | Results are presented of an experimental investigation of the characteristics of NACA submerged inlets on a model of a fighter airplane for Mach numbers from 0.30 to 0.875. The effects on the ram-recovery ratio at the inlets of Mach number, angle of attack, boundary-layer thickness on the fuselage, inlet location, and boundary-layer deflectors are shown. The data indicate only a slight decrease in ram-recovery ratio for the inlets ahead of or just behind the wing leading edge as Mach number increased, but showed large decreases at high Mach numbers for the inlets aft of the point of maximum thickness of the wing. |
| File Size | 18429449 |
| Page Count | 46 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930085451 |
| Archival Resource Key | ark:/13960/t6tx7nw49 |
| Language | English |
| Publisher Date | 1948-11-17 |
| Access Restriction | Open |
| Subject Keyword | Inlets, Side - Ducted Bodies Inlets, Side - Submerged 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 |
