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Pressure recovery, drag, and subcritical stability characteristics of three conical supersonic diffusers at stream mach numbers from 1.7 to 2.0
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1952 |
| Description | A study of a 20 degree and a 25 degree half-angle high mass-flow ratio conical supersonic inlet was made on a 16-inch ram jet in the 8- by 6-foot supersonic tunnel. A greater range of stable subcritical operation was obtained with the low mass-flow ratio inlets; a greater range was obtained with the 25 degree than with the 20 degree half-angle low mass-flow ratio inlet. The high mass-flow ratio inlet had the least drag. |
| File Size | 15555842 |
| Page Count | 36 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930086890 |
| Archival Resource Key | ark:/13960/t18m1nj5k |
| Language | English |
| Publisher Date | 1952-02-27 |
| Access Restriction | Open |
| Subject Keyword | Diffusers, Supersonic Engines, Ram Jet Air Inlets - Nose, Annular Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |