1.6.22 · D2Oscillations & Waves

Visual walkthrough — Shock waves — Mach number, Mach cone — - CRITICAL for rockets -

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Step 1 — One source, one ripple

WHAT. Put a single point in still air. At one instant it gives a tiny push — a pressure pulse. That pulse spreads outward as a growing sphere (a circle if we draw the flat cross-section).

WHY start here. Everything about shocks is just many of these ripples added up. If you understand one ripple's size, you understand the whole cone. A ripple is our atom.

PICTURE. The dot is the source. The blue circle is the wavefront — the set of all points the pulse has reached so far. Its radius grows because sound moves at a fixed speed.

Figure — Shock waves — Mach number, Mach cone — - CRITICAL for rockets -

Reading the figure term by term:

Every symbol here is on the picture: is the blue radius, is the outward arrow, is "how long ago." The ripple is bigger the longer we wait — that is the whole content of .


Step 2 — The source moves and keeps emitting

WHAT. Now let the source glide to the right at speed , dropping a fresh ripple at every instant, like breadcrumbs. Each older ripple is bigger (it has had more time to grow); each newer one is smaller.

WHY. A moving whistle doesn't ring once — it rings continuously. The pattern those overlapping ripples make is the physics. We need to see where they crowd together.

PICTURE. Four ripples emitted at four past positions. Notice the oldest (leftmost) is the largest circle, the newest is a dot. The source keeps up front.

Figure — Shock waves — Mach number, Mach cone — - CRITICAL for rockets -

The distance the source has travelled since a ripple was dropped:

So at any moment we are comparing two lengths that both grow with : the ripple's radius and the source's travel . The race between these two is the entire story.


Step 3 — The subsonic case: source stays inside its ripples

WHAT. Suppose the source is slower than sound, (so ). Then in the same time , the ripple () outreaches the source (). The source is always inside every ripple it made.

WHY show this first. To appreciate the shock we must see the calm before it. Subsonically the ripples bunch up ahead (that forward crowding is the Doppler effect) but they never form a sharp wall — there is always a gap, no common edge.

PICTURE. The moving dot sits inside all its circles. Ripples are denser in front, sparser behind, but nowhere do they touch a shared line.

Figure — Shock waves — Mach number, Mach cone — - CRITICAL for rockets -

No pile-up surface here. Hold this contrast — the next step flips it.


Step 4 — The supersonic case: source escapes its ripples

WHAT. Now make the source faster than sound, (so ). In the same , the source travels farther () than the ripple's radius (). The source pops outside its own wavefront.

WHY this is the turning point. Once the source is ahead of its ripples, all the ripples get left behind together — and their outer edges can share a single straight tangent. That shared tangent is where every ripple's crest lands at once.

PICTURE. The dot has run out past the leftmost part of every circle. A green straight line just grazes (is tangent to) all the circles at once. That green line is the shock front.

Figure — Shock waves — Mach number, Mach cone — - CRITICAL for rockets -


Step 5 — Pull out the right triangle

WHAT. Freeze the picture at one moment. Mark three points:

  • = where a ripple was emitted at time .
  • = where the source is now, at time (it has moved off along its track).
  • = the tangent point: the single spot where the shock line just touches (grazes) that ripple. Draw the ripple's radius from its centre straight out to — because a radius always meets a tangent at a right angle, this radius hits the shock line at .

These three points , , form a right triangle, with the right angle sitting at .

WHY a triangle, and why this one. We want a number for the cone's angle. The cleanest way to trap an angle is inside a right triangle, because then the angle is locked to a ratio of two sides — no calculus, just the shape. This is exactly the kind of side-ratio question the sine function was invented to answer.

PICTURE. Triangle : apex angle at , right angle at , the two known sides labelled.

Figure — Shock waves — Mach number, Mach cone — - CRITICAL for rockets -

Naming the three parts of this triangle:

  • Hypotenuse — the long slanted side, how far the source went.
  • Opposite side — the ripple radius (from centre to tangent point ), standing across from angle .
  • Angle — the Mach angle, sitting at the source apex ; it is the half-opening of the cone.

Step 6 — Read off the angle; watch time cancel

WHAT. Put the two side lengths into the sine ratio.

WHY. This converts the picture into a formula we can compute with.

The on top and bottom cancels — this is the quiet miracle. Both sides grow at the same rate as time passes, so their ratio never changes.

PICTURE. Two triangles from two different moments (small and large) laid over each other: different sizes, identical angle . The cone opening is fixed for all time.

Figure — Shock waves — Mach number, Mach cone — - CRITICAL for rockets -

Now use the Mach number defined back in Step 2, . The fraction is exactly turned upside down, i.e. :


Step 7 — Every case, including the broken ones

WHAT. Test the formula at the boundaries, because a formula you trust must survive its extremes.

WHY. A physicist never accepts a result without pushing it to , , and . The formula should either give something sensible or tell you the physics is impossible.

PICTURE. Three cones side by side: wide at low supersonic , thin at high , and a flat plane at .

Figure — Shock waves — Mach number, Mach cone — - CRITICAL for rockets -
  • exactly (source at sound speed): , so . The cone opens all the way into a flat wall perpendicular to the motion — the "sound barrier." The ripples all pile onto one plane right at the nose.
  • (hypersonic): , so — an infinitely thin, sharply swept cone hugging the flight path. Faster ⇒ skinnier. (This is the regime of Wave drag and aerodynamic heating on re-entry.)
  • (subsonic): . But a sine can never exceed no real angle solves it. The math itself refuses, matching Step 3: the source stays inside its ripples, so no cone exists. The equation isn't broken; it is telling you the truth.

The one-picture summary

Everything on one canvas: several growing ripples, the source out front, the tangent cone, the right triangle with and , and the boxed result. If you can redraw this from memory, you own the derivation.

Figure — Shock waves — Mach number, Mach cone — - CRITICAL for rockets -
Recall Feynman retelling of the whole walkthrough

Drop a stone: one ripple ring grows outward at the sound speed (Step 1). Now walk while tapping the water — you leave a trail of rings, big old ones behind, tiny new ones under your feet (Step 2), and we keep score with , how your speed compares to the ripples'. Walk slowly () and the rings surround you; you're always inside them (Step 3). Sprint faster than the ripples () and you burst out ahead — now all the ring edges line up along one straight slanted wall dragging behind you in a V (Step 4). Pin that V's angle inside a right triangle: one side is how far a ripple grew (), the slanted side is how far you ran (), and they meet at the tangent point (Step 5). Their ratio is the sine of the V's half-angle, and the times cancel so the V never changes shape: (Step 6). Push it: at exactly sound speed the V flattens into a wall; far above it the V gets razor-thin; slower than sound the formula demands an impossible sine, which is nature's way of saying "no shock down here" (Step 7). That skinny V of squished air is the sonic boom you hear as it sweeps past.

Connections

  • Speed of sound in a medium — supplies , the ripple-edge speed in Step 1.
  • Doppler effect — the forward crowding of ripples in the subsonic Step 3.
  • Superposition & constructive interference — why the tangent line in Step 4 becomes a shock.
  • Wave drag and aerodynamic heating — the thin hypersonic cone of Step 7.
  • De Laval nozzle — where supersonic is engineered on purpose.
  • Compressible flow / Bernoulli limits — why breaks simple flow assumptions.