There is no "high Speed stall" you may be confusing it with flow separation due to shock waves or accelareted stall due to an increase of the load factor(wich happens for example if you pull too hard on the ctrl column at high airspeed).
A
stall is a condition in
aerodynamics and
aviation where the angle between the wing's
chord line and the relative wind, defined as the angle of attack, exceeds the critical angle of attack. This angle is typically 12 to 15 degrees for many subsonic airfoils. The critical angle of attack is the angle of attack on the
lift coefficient versus angle-of-attack curve at which the maximum lift coefficient occurs, and it defines the boundary between the wing's
linear and
nonlinear regimes. Flow separation begins to occur at this point, decreasing lift, increasing
drag, and changing the wing's
pitching moment. A fixed-wing aircraft during a stall may experience buffeting, a change in pitching moment (nose up or nose down depending on
tailplane configuration), and changes in most stability derivatives. Most aircraft are designed to have a gradual stall with characteristics that will warn the pilot and give the pilot time to react. For example an aircraft that does not buffet before the stall may have a
stick shaker installed to simulate the feel of a buffet by vibrating the stick fore and aft. The critical angle of attack can at 1g only be attained at low airspeed. Attempts to increase the angle of attack at higher airspeeds merely cause the aircraft to climb.
Consequently at 1g, stalling occurs only when the aircraft is flying slowly.