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An analytical study of the comparative performance of six air-induction systems for turbojet-powered airplanes designed to operate at mach numbers up to 2.0
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1953 |
| Description | A study is presented of inlet designs and aerodynamic characteristics of air-induction systems intended for operation with a turbojet engine operating with a constant-volume air-flow process. Two-dimensional inlet designs similar to those discussed in NACA RM A52C14, plus a fixed-geometry inlet with a convergent-divergent diffuser, and an additional variable-geometry inlet are considered for Mach numbers from 0.85 to 2.0 from sea level to the stratosphere. For best performance throughout this range of Mach numbers and altitudes, it was shown that the geometry of the inlet must be such as to insure a high pressure recovery, as well as to provide for a variable entrance area. The inlets are compared on the basis of a drag evaluation neglecting viscosity. |
| File Size | 3004112 |
| Page Count | 47 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930087828 |
| Archival Resource Key | ark:/13960/t9284pc7r |
| Language | English |
| Publisher Date | 1953-10-09 |
| Access Restriction | Open |
| Subject Keyword | Diffusers, Subsonic Air Inlets - Nose, Central Air Inlets, Scoops Diffusers, Supersonic 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 |
