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At which flow regime does aerodynamic quantities such as coefficient of pressure, lift become independent of Mach number?

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At which flow regime does aerodynamic quantities such as coefficient of pressure, lift become independent of Mach number?

(a) Subsonic

(b) Supersonic

(c) Transonic

(d) Hypersonic

This question was posed to me in an interview.

The question is from Mach Number Independence in chapter Transonic and Hypersonic Flows of Aerodynamics

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Right choice is (d) Hypersonic

To elaborate: For flows above Mach number 5 i.e. hypersonic flow, it is seen that the aerodynamic quantities such as coefficient of pressure, coefficient of life and wave drag become independent of the Mach number. This aspect was even described by Newton while formulating his Newtonian theory which states the coefficient of pressure is independent of Mach number at hypersonic speed.

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