// multi-utility computation suite · offline · instant · precise
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sci.hypersonic-Mach-heating Calculator
Calculates aerodynamic heating at hypersonic Mach numbers using the Fay-Riddell stagnation point heat flux equation and Chapman correlation. At Mach 25 re-entry, stagnation heating exceeds 10 MW/m² — Space Shuttle nose cap temperatures reached 1,650 °C, requiring reinforced carbon-carbon (RCC) material.
Inputs
M Mach
Count of items or occurrences.
T Inf K
Thermal state of the substance. Check whether the formula needs Celsius, Fahrenheit, or Kelvin (K = °C + 273.15).
R Nose M
Distance from centre to edge of a circle. Radius = diameter / 2.
Rho Inf Kg M3
Mass per unit volume (kg/m³). Water: 1,000. Air: 1.225. Steel: 7,850. Affects buoyancy, flow, and structural loads.
Results
stagnation temperature T_stag (K)
The value at the specified point or condition.
freestream velocity V (m/s)
Reference formula or conversion factor shown for context.
stagnation heat flux q̇ (MW/m²)
The value at the specified point or condition.
T_stag = T∞(1 + (γ−1)/2·M²)
Reference formula or conversion factor shown for context.
q̇ = 1.83×10⁻⁴·√(ρ/R)·V³ (W/m²)
Reference formula or conversion factor shown for context.