In compressible flows, particularly at high speeds, dynamic pressure is related to Mach number (\(M\)) and static pressure (\(p\)). For an ideal gas, the relationship is given by \(q = \frac{1}{2} \gamma p M^2\), where \(\gamma\) is the ratio of specific heats. This formulation is crucial for supersonic and hypersonic aerodynamics, where fluid density changes significantly.
