Parameters
Presets
Mass m
1.0 kg
Drag coefficient Cd
0.47
Sphere: 0.47 / Streamlined: 0.04 / Flat plate: 1.17
Cross-sectional area A
0.0100 m²
Air density ρ
1.225 kg/m³
Sea level: 1.225 / 10 km alt.: 0.41 / Vacuum: 0
Initial height h₀
200 m
Initial velocity (downward) v₀
0.0 m/s
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Terminal velocity v_t [m/s]
—
Landing time [s]
—
Landing speed [m/s]
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Time to terminal v [s]
With air drag
Vacuum (Cd=0)
Terminal velocity
Velocity v(t) [m/s]
Altitude h(t) [m]
Theory
$$m\frac{dv}{dt} = mg - \frac{1}{2}C_d \rho A v^2$$Terminal velocity (when $dv/dt = 0$):
$$v_t = \sqrt{\frac{2mg}{C_d \rho A}}$$Vacuum fall ($C_d=0$): $v = v_0 + gt$, $h = h_0 - v_0 t - \frac{1}{2}gt^2$
Numerical integration: Euler method (Δt = 0.01 s) over all time steps
CAE Connection: Initial velocity setting for drop impact analyses (LS-DYNA / Abaqus Drop Test) / Cd validation for automotive aerodynamic drag (CFD) / preliminary terminal velocity estimation for spacecraft re-entry / coupling with Reynolds number calculations.