2 Aerodynamics
135
Fig. 2.70 Relationship between oblique shock angle and cleavage angle at different
Mach numbers
Fig. 2.71 The change curve of the shock velocity obtained from the continuum
hypothesis
2.6 Solution of Compressible Flow
In the flow around the aircraft, whether the compressibility of air must be
considered depends on whether the pressure change in the flow process can
cause significant density change. When Ma number is less than 0.3, the
density change is less than 5% and the change in pressure coefficient is less
135
Fig. 2.70 Relationship between oblique shock angle and cleavage angle at different
Mach numbers
Fig. 2.71 The change curve of the shock velocity obtained from the continuum
hypothesis
2.6 Solution of Compressible Flow
In the flow around the aircraft, whether the compressibility of air must be
considered depends on whether the pressure change in the flow process can
cause significant density change. When Ma number is less than 0.3, the
density change is less than 5% and the change in pressure coefficient is less