No one has answered why; only answers have been "no marketable product".
There are several technical reasons why, none of which have been been subject to any technological advances in half a century.
1) There's a buffer factor where burning fuel adds a thousand degrees (or whatever) to temp of the air in the engine and steel / titanium / classified will melt several hundreds of degrees above that. Most all jet engines can only work with subsonic airflow. Supersonic aircraft use exotic inlet designs that are inefficient but can convert fast air into very hot compressed air. Somewhere around mach 2 to mach 4 the inlet air temp plus the heat of burning fuel will melt any metal turbine blade. You can pay a lot of money to get a couple mach numbers but fundamentally cheap steel gets you mach 2 and price is no object aerospace material tops out in the mid mach 3 range. True lab experimental materials might survive mach 4 temps, maybe. You just can't get a usable thrust to weight ratio inlet design that works above mach 4 or so.
2) Second aerodynamic problem is if you define "fly" as a lift to drag ratio better than a lawn dart, optimizing wing sweep etc for mach 3+ means its a truly awful performer below 5000 feet or so. Its hard to make an aircraft that actually "flies" above mach 4. Space shuttle L/D ratio was around or below 1:1. Essentially things flying thru the air above mach 4 don't fly in the sense of wings producing lift, they're ballistic trajectory like a missile or bullet, don't bother slapping wings on them.
None of the above can be solved with faster computer cycles. Titanium still melts at the same temp, etc.