British Aerospace AST.
 

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Hi! ATSF design evolution. ATSF1(1978), ATSF2(1983) and ATSF3(1989).
 

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In these pictures, we can see ATSF model with canard and circular engine air intake.
 

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Hi! British Aerospace AST study.

Mid-tandem fan engine (Rolls-Royce and SNECMA proposed non reheat mid tandem fan engine for AST)

In the mid-tandem fan concept, a high specific flow single stage fan is located between the high pressure (HP) and low pressure (LP) compressors of a turbojet core. Only bypass air passes through the fan. The LP compressor exit flow passes through passages within the fan disc, directly underneath the fan blades. Some bypass air enters the engine via an auxiliary intake. During take-off and approach the engine behaves much like a conventional turbofan, with an acceptable jet noise level (i.e., low specific thrust). However, for supersonic cruise, the fan variable inlet guide vanes and auxiliary intake close to minimize bypass flow and increase specific thrust. In this mode the engine acts more like a 'leaky' turbojet (e.g. the F404).(wikipedia)
 

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Research situation in Europe
Research on future HSCT engines was conducted mainly by RR and SNECMA, with the participation of MTU and Fiat, and a MidTandem Fan (MTF) type Variable Cycle Engine based on SNECMA's MCV99 was selected as the basic engine. During takeoff and climb, both fans flow maximum airflow, and the engine operates as a turbofan with a bypass ratio of about 2. At supersonic speeds of Mach 2, the air to the Mid-Fan is closed, and the engine behaves as an engine with a bypass ratio of about 1. Also, from the viewpoint of noise reduction, it is considered sufficient to use an improved two-dimensional nozzle used in the Concorde/Olympus593, rather than a huge Mixer-Ejector Nozzle.
 

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Hi!

 

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The explanation (little strange) of this picture is as follows, and this model looks like British AST or French ATSF very much.

Engineer Dave Hahne inspects a 1/10th scale model of the MACH 2.2 supersonic transport concept, designed by the Douglas Aircraft Company, in the Full-Scale Tunnel. The test produced a large database of aerodynamic data for low-speed performance, stability, and control, as well as pressures on the wing leading edge. The primary goal of the test was to compare the aerodynamic performance of a 20-year-old constant-chord leading-edge flap designed by computational methods. Photo taken November 23, 1992.
NASA


 

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According to the explanation of this picture, this model is AST. (But without canard)

Another explanation.(from Cave of the winds)
A wind-tunnel model of a supersonic transport undergoing testing at NASA Langley Research Center on January 17, 1975. The 30 foot by 60 foot tunnel was used in the mid 1970s to test the model at low speeds
 

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