What Is the Sutton-Graves Hypersonic Stagnation Heat Flux Calculator?
Sutton-Graves correlation predicts stagnation convective heating during atmospheric entry.
How Does the Sutton-Graves Hypersonic Stagnation Heat Flux Calculator Work?
Heat flux scales directly with V^3 and inversely with the square root of nose bluntness radius Rn.
Sutton-Graves Hypersonic Stagnation Heat Flux Calculator Formula & Variables
The core mathematical equation utilized by this calculator is expressed as:
\dot{q}_s = k \sqrt{\frac{\rho_\infty}{R_n}} V_\infty^3, \quad T_{eq} = \left( \frac{\dot{q}_s}{\varepsilon \sigma} \right)^{1/4}
Sutton-Graves convective heat flux and radiation equilibrium surface temperature.
How to Use the Sutton-Graves Hypersonic Stagnation Heat Flux Calculator
- Input freestream density, vehicle velocity, nose radius, and planetary constant.
Step-by-Step Example Calculation
Earth LEO Entry Capsule
Input Values:
freestreamDensityKgPerM3:0.001
velocityMPerS:7500
noseRadiusMeters:0.5
planetaryConstantK:0.00017415
Worked Steps: Predicts peak convective heat flux and thermal radiation equilibrium temperature.
Understanding Your Result
Gives heat flux in W/cm² and MW/m² plus equilibrium radiative wall temperature.
Factors That Affect the Result
- Increasing bluntness (larger Rn) reduces stagnation convective heating significantly.
When Should You Use This Calculator?
- Thermal Protection System (TPS) thickness optimization and trajectory trade studies.
Assumptions & Limitations
- Applies to convective stagnation point; excludes radiative shock layer emission.
Frequently Asked Questions
Calculation Accuracy & Reference Note
Standard engineering reference validated across Apollo, Shuttle, and Orion flight programs.