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Normal Shock — Compressible Flow
1 to 1.45 · 1.40 dimensionless, 1 dimensionless, 1 dimensionless
Normal shock relations — discontinuous property changes across a stationary shock — tabulated property ratios as a function of Mach number. Calculated for specific heat ratio γ = 1.40 (air at standard conditions). Covers 96 Mach numbers from 1 to 50, with all relevant property ratios (T/T*, p/p*, ρ/ρ*, p₀/p₀*, A/A*, fL*/D, etc.) for design and analysis of compressible duct flow.
- r-1Mach Number: 1mach number 1
- 1.05Mach Number: 1.05mach number 1.05
- 1.1Mach Number: 1.1mach number 1.1
- 1.15Mach Number: 1.15mach number 1.15
- 1.2Mach Number: 1.2mach number 1.2
- 1.25Mach Number: 1.25mach number 1.25
- 1.3Mach Number: 1.3mach number 1.3
- 1.35Mach Number: 1.35mach number 1.35
- 1.4Mach Number: 1.4mach number 1.4
- 1.45Mach Number: 1.45mach number 1.45