For Figure 3, these values are M = 3.0 and 0.4752, which can be found the normal shock tables listed in most compressible flow textbooks.
22.
A ) exploit a combination of conical shock wave / s and a normal shock wave to improve pressure recovery at high supersonic flight speeds.
23.
As the exhaust passes through the normal shock wave, its temperature increases, igniting excess fuel and causing the glow that makes the shock diamonds visible.
24.
The Concorde employed an external-compression inlet, using a series of oblique shocks followed by a normal shock to slow the flow sufficiently for the turbojet engine.
25.
Conical shock wave / s are used to reduce the supersonic Mach number at entry to the normal shock wave, thereby reducing the resultant overall shock losses.
26.
For Figure 5, these values are " M " = 3 and 0.4752, which can be found the normal shock tables listed in most compressible flow textbooks.
27.
The relationship between the post normal shock density, \ rho _ 2, and the upstream ambient density, \ rho _ 1 is shown next in the tables.
28.
Early supersonic aircraft jet engine intakes were designed using compression from a single normal shock, but this approach caps the maximum achievable Mach number to roughly 1.6.
29.
If the inlet flow is not match, it may become unstable with the normal shock wave in the throat suddenly moving forward beyond the lip, known as inlet unstart.
30.
Finally, the ratio of stagnation pressures is shown below where p _ { 01 } is the upstream stagnation pressure and p _ { 02 } occurs after the normal shock.
