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ATYA // SCHLIEREN TEST FACILITY
ALT: FL480STATUS: SUPERSONIC
MACH VELOCITYM 1.45
Mach: 1.450.75 - 2.60
Angle of Attack (α): 3.5°-6° to +14°
Reheat Throttle: 75%Afterburner
SHOCK ANGLE (β)
44°
DYN PRESSURE (q)
48 kPa
STAG TEMP (T₀)
409 K
REHEAT STATUS
ACTIVE REHEAT
OPTICS:

Aerospace WebGL Engineering

Concept #1: The Supersonic Schlieren Fluid Simulation

← Back to Engineering
01 // OPTICS

Schlieren Knife-Edge Cutoff

Schlieren photography reveals variations in air density (∇ρ) by intercepting refracted light rays with an optical knife edge. In our shader, the light intensity is directly proportional to the directional density gradient:

I = I₀ · (1 + k · (∇ρ · n̂_knife))
02 // THERMODYNAMICS

Prandtl-Glauert Vapor Cone

In transonic flight (M ≈ 0.95 - 1.2), acceleration over the wing and canopy creates localized low-pressure regions. The resulting temperature drop causes ambient moisture to condense into a dynamic, billowing vapor cone rendered via volumetric FBM noise.

C_p ∝ 1 / √( |1 - M²| )
03 // PROPULSION

Mach Diamond Exhaust Cells

Supersonic engine exhaust creates standing wave patterns where oblique shocks reflect internally between the plume boundary and centerline. The spacing of these glowing diamond cores contracts and expands based on jet exhaust Mach number:

λ_diamond ≈ 2 · r_jet · √( M_jet² - 1 )

PILOT INTERACTION GUIDE

Mouse Y (Vertical): Tilts the vehicle’s Angle of Attack (α). Notice how the shock on the underside steepens as compression increases, while suction above enhances the vapor envelope.
Mouse X (Horizontal): Adjusts oncoming Mach velocity. As speed increases, the Mach cone angle (μ = arcsin(1/M)) sweeps back tighter.
Punch Afterburner: Simulates supersonic throttle surge, flaring the exhaust plume and tightening the shock envelope.
Optics Modes: Switch between our signature Atya brand amber palette, authentic NASA wind tunnel monochrome, or CFD isobar pressure maps.