Model atmospheric entry heating with practical engineering inputs. Track pressure, temperature, and shield demand clearly. Plan robust thermal protection using fast, transparent scenario analysis.
| Scenario | Velocity (m/s) | Density (kg/m³) | Nose Radius (m) | Duration (s) | Approx. Heat Flux (W/cm²) |
|---|---|---|---|---|---|
| Low Ballistic Return | 6,800 | 0.00040 | 0.90 | 320 | 376.92 |
| Crew Capsule Entry | 7,800 | 0.00080 | 0.75 | 420 | 779.85 |
| High Energy Return | 10,900 | 0.00120 | 0.60 | 510 | 3,352.40 |
These example values illustrate how strong velocity changes dominate stagnation heating during atmospheric entry.
1) Stagnation point convective heat flux:
q̇ = k × √(ρ / Rn) × V³
Here, q̇ is stagnation heat flux, k is the selected correlation constant, ρ is local density, Rn is nose radius, and V is velocity.
2) Integrated heat load:
Q = q̇ × t
This provides the estimated thermal energy per unit area over the chosen heating duration.
3) Dynamic pressure:
q = 0.5 × ρ × V²
4) Ballistic coefficient:
β = m / (Cd × A)
5) Adiabatic wall temperature:
Taw = T∞ × [1 + r × ((γ − 1) / 2) × M²], where r = Pr^(1/3)
6) Radiative equilibrium wall temperature:
Teq = (q̇ / (ε × σ))^(1/4)
This tool is meant for preliminary design screening, trade studies, classroom use, and sensitivity checks. Detailed mission design still needs trajectory-coupled aerothermodynamic analysis.
It estimates stagnation heat flux, integrated heat load, dynamic pressure, ballistic coefficient, adiabatic wall temperature, radiative equilibrium temperature, and an approximate thermal protection margin for reentry screening studies.
The calculator uses a Sutton-Graves style convective heating relationship. It is widely used for preliminary entry analysis because it links heat flux strongly to velocity, density, and nose radius.
Heat flux scales with the cube of velocity in this model. That means modest speed increases can raise thermal loads dramatically, making entry corridor control and trajectory design very important.
A larger nose radius spreads heating over a broader region and usually lowers peak stagnation heating. Blunter shapes often reduce local peak heat flux, though they can change aerodynamic behavior.
No. It is an engineering approximation based on recovery temperature and radiative balance assumptions. Real surfaces may experience catalytic, radiative, ablative, and material-response effects not captured here.
Adjust it when you want to match a particular correlation, unit convention, planet, or validated internal method. Keeping it editable makes the calculator useful for sensitivity studies and teaching.
It compares the calculated integrated heat load with the allowable value you entered. A positive margin suggests reserve capacity, while a negative margin indicates the design target is exceeded.
No. It is best for concept design, comparisons, and quick checks. Final thermal protection design should rely on high-fidelity trajectory data, gas chemistry models, and material response tools.
Important Note: All the Calculators listed in this site are for educational purpose only and we do not guarentee the accuracy of results. Please do consult with other sources as well.