Distinguish static and total
Static pressure rises across the shock, while total pressure falls. Pressure recovery is not the same as static compression.
03 / COMPRESS · Aerodynamics
Normal Shocks & Total-pressure Loss
Compressible flowBrowser calculation
Move from a weak to a stronger normal shock. Follow the mass, momentum and energy crossing one stationary discontinuity.
COMPRESSION HAS AN IRREVERSIBLE COSTLIVE B
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The shock is stationary at the centre. Particles represent equal mass flux; downstream spacing contracts in proportion to the calculated speed. The sharp jump has no resolved internal thickness.
Account for energy
Kinetic energy becomes internal enthalpy. With no heat or work, total temperature stays constant.
Approach Mach one
At M₁ = 1 the jump vanishes. This is the continuous limiting case, not a finite-strength shock.
CALCULATED FROM THE SAME MODEL
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Equations, assumptions and topic connections
Physical model
Steady 1D stationary normal shock in a calorically perfect gas. R = 287.05 J/(kg K), constant selected γ. No heat, shaft work, viscous thickness, chemistry, oblique shock or inlet matching is solved. The M = 1 endpoint is the no-jump limit.
ρ₁u₁ = ρ₂u₂; p₁ + ρ₁u₁² = p₂ + ρ₂u₂²; cpT₁ + u₁²/2 = cpT₂ + u₂²/2. p₂/p₁ = [2γM₁² − (γ−1)]/(γ+1); ρ₂/ρ₁ = (γ+1)M₁²/[2+(γ−1)M₁²].
Topic connections
S06 · PDF pp. 43–67; candidate diagrams pp. 48, 58, 62, 65–67. compressible-flow foundation; inlet/nozzle bridge. No lecture artwork reused.
Original schematic diagrams. No manufacturer performance, certification or maintenance-authorisation claim. Numerical verification checks the declared model; it is not experimental validation. Model version: course-foundations-v1.