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Transonic off-design drag and performance of an axisymmetric inlet with 40 percent internal contraction on design
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Meleason, E. T. Woollett, R. R. Choby, D. A. |
| Copyright Year | 1974 |
| Description | An experimental investigation determined the drag and pressure performance of an axisymmetric supersonic inlet when operated in the transonic speed range. The inlet configuration was derived from a Mach 2.5 mixed compression inlet design with assumed variable geometry. At typical engine airflows the drag coefficient varied from 0.057 to 0.192 when the Mach number changed from 0.80 to 1.27. The presence of a wing simulator resulted in a sizable increase in total drag at Mach 1.2. This interference drag, which is roughly a 0.1 increase in drag coefficient, originates equally from an increase in both additive and cowl pressure drag. |
| File Size | 6906948 |
| Page Count | 55 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19740023304 |
| Archival Resource Key | ark:/13960/t3b03xk14 |
| Language | English |
| Publisher Date | 1974-08-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Aerodynamic Drag Transonic Flow Engine Inlets Aerodynamic Interference Flow Characteristics Inlet Flow Variable Geometry Structures Axisymmetric Flow Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
