🔥 Hypersonic Aerodynamic Heating (Sutton-Graves)
Calculate hypersonic stagnation convective heat flux (kW/m²), radiative equilibrium wall temperature (Trad), and stagnation enthalpy using Sutton-Graves and US 1976 atmosphere.
⚡ Fortran 90 Engine
Double Precision (IEEE 754)
✓ ISO / ASME Validated
📊 Solver Telemetry
● ACTIVE
👁️ Consultations
15
⚡ Calculs faits
14
💾 Téléchargements
337
📦 Code Fortran
4.4 KB
📅 Mise en service
Jun 2026
⏱️ Latence
< 1 ms
🔥 Hypersonic Bow Shock Wave & Stagnation Point Plasma Sheath
Real-time visual simulation of detached bow shock, stagnation plasma layer & radiative thermal glow📝 Configuration & Presets
🛰️ LEO Capsule (7.5 km/s)
🚀 Wave-Rider Glide (Mach 11)
🌕 Lunar Return (11 km/s)
✈️ Scramjet Cruise (Mach 7)
Sutton-Graves Heating Formulations:
• Stagnation Flux: q̇₀ = kSG · √(ρ∞ / Rn) · V∞³ [W/m²]
• Radiative Wall Temp: Trad = ( q̇₀ / (ε · σ) )1/4 [K]
• Total Enthalpy: h₀ = cp T∞ + ½ V∞² [MJ/kg]
• Post-Shock Pressure: P₀₂ ≈ 0.92 · ρ∞ · V∞² [kPa]
• Stagnation Flux: q̇₀ = kSG · √(ρ∞ / Rn) · V∞³ [W/m²]
• Radiative Wall Temp: Trad = ( q̇₀ / (ε · σ) )1/4 [K]
• Total Enthalpy: h₀ = cp T∞ + ½ V∞² [MJ/kg]
• Post-Shock Pressure: P₀₂ ≈ 0.92 · ρ∞ · V∞² [kPa]
📊 Aerodynamic Heating Results
📊 Output Summary
Stagnation Point Heat Flux (q̇₀)
q̇₀ = 1,248 kW/m² (1.25 MW/m²)
Radiative Equilibrium Temp: 1,963 °C (2,236 K)
Mach 23.9
Radiative Wall Temp (Trad)
1,963 °C
ε = 0.88
Stagnation Recovery Enthalpy
28.37 MJ/kg
Total Energy
Stagnation Impact Pressure (P₀₂)
14.92 kPa
0.149 bar
Free-Stream Air Density (ρ∞)
2.88e-4 kg/m³
At Z = 60.0 km
📈 Stagnation Heat Flux q̇₀ (kW/m²) vs Altitude Z (km)
📉 Radiative Wall Temp T_rad (°C) vs Nose Radius R_n (m)
================================================================= THERMOFLUIDCALC — HYPERSONIC AERODYNAMIC HEATING REPORT ================================================================= Case Title : Low Earth Orbit (LEO) Manned Capsule Atmospheric Reentry Flight Altitude / Velocity : 60.00 km / 7500.0 m/s (Mach 23.88) Nose Radius / Emissivity : 1.000 m / 0.88 Atmospheric Properties : rho = 2.8833e-4 kg/m3, T = 245.4 K, P = 20.31 Pa ----------------------------------------------------------------- STAGNATION HEAT FLUX (q0) : 1,247.5 kW/m2 (1.248 MW/m2) Radiative Equilibrium Trad : 1,962.9 °C (2,236.1 K) Stagnation Enthalpy (h0) : 28.37 MJ/kg Post-Shock Stagnation P02 : 14.92 kPa (0.149 bar) =================================================================
📘 Calculation Methodology & Hypersonic Aerothermodynamic Standards
Sutton-Graves Convective Model
Derived from boundary layer boundary solutions with high-temperature gas dissociation equilibrium. Convective heat flux scales inversely with the square root of nose radius $R_n$:
q̇₀ = 1.7415 × 10⁻⁴ · √(ρ∞ / Rn) · V∞³
Radiative Surface Equilibrium
Assuming negligible interior conduction into the Thermal Protection System (TPS), wall temperature reaches radiative balance: $q_{conv} = \epsilon \sigma T_{rad}^4$.
Key Engineering Assumptions
- 1976 US Standard Atmosphere piecewise thermodynamic equations.
- Axisymmetric spherical / cylindrical blunt stagnation point.
- Equilibrium laminar hypersonic boundary layer.