Numerical Investigation On Supersonic Inlet With Realistic Bleed And Bypass Systems
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Numerical Study of Control of Dynamic Properties of a Supersonic Inlet Using Bypass Bleed
| Author | : Clarence W. Matthews |
| Publisher | : |
| Total Pages | : 44 |
| Release | : 1971 |
| Genre | : Automatic control |
| ISBN | : |
Survey of CFD Applications for High Speed Inlets
| Author | : Keith E. Numbers |
| Publisher | : |
| Total Pages | : 60 |
| Release | : 1994 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
A comprehensive review of techniques and methods for applying computational fluid dynamics (CFD) analysis to high speed inlets and related flows is provided via an extensive literature survey of such applications. Topics covered include governing equations, numerical integration schemes, boundary conditions, gridding requirements, and turbulence models. Results of applications from the literature survey shed light on the relative success of the techniques being used throughout the industry. (AN).
Experimental Investigation of a Large-scale, Two-dimensional, Mixed-compression Inlet System
| Author | : Norman D. Wong |
| Publisher | : |
| Total Pages | : 68 |
| Release | : 1971 |
| Genre | : Jet engines |
| ISBN | : |
A large-scale, variable-geometry inlet model with a design Mach number of 3.0 was tested at Mach numbers from 1.55 to 3.2. Variable features of the inlet for off-design operation are an adjustable-height ramp system and a translating cowl. This report presents experimental results for a diffuser and boundary-layer bleed configuration which was optimized at the design Mach number. Overall performance was high with throat-mounted vortex generators, which were effective in reducing flow distortion in the subsonic diffuser at the higher Mach numbers.
Investigation of Fixed-geometry Supersonic Inlets with Bypass Ducts for Matching Turbojet-engine Air-flow Requirements Over a Range of Transonic and Supersonic Speeds
| Author | : Abraham Leiss |
| Publisher | : |
| Total Pages | : 50 |
| Release | : 1958 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
A method is presented to design a supersonic inlet that will match turbojet-engine air mass-flow requirements over a wide Mach number range. Two types of bypasses were investigated; one had a 360 degree annular cowling and the other had twin slotted ducts. Three models were flight tested. Two of the models, which had bypass ducts, were also ground tested. The bypass models had higher external drags. Both bypass models approximated a typical turbojet-engine air mass-flow requirement between Mach numbers 1.0 and 2.0. The flight tests covered a Reynolds number range from 200,000 to 800,000 and a Mach number range from 0.8 to 1.95.
