The Bristol Type 188 was limited to Mach 1.88 by a combination of intake unstart’s (due time an intake transducer being incorrectly specified) and fuel endurance (the engine fuel consumption was too high as a result of an early cessation of development).

I’ve seen design analysis and wind tunnel testing which showed a positive stability margins at Mach 2.8 with the comment that the analysis and testing was considered conservative. It was hoped the real aeroplane flight test could in its full developed form, would exceed Mach 3. From memory there was a note that this was the windshield limit.
 
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From Interavia 1961,

as in reply # 15,but that's clearer view.
 

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From Interavia 1961,

the article.
 

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From this source.
 

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