Thanks folks.
Let’s set some ground rules – pun intended.
Two things can be deadly:
- The ground
- Burning up in the atmosphere.
Consider three types of ground – hard ground, water-like liquid, and soft ground.
By soft ground I mean deep snow or panes of glass (unlaminated). Why glass, because it’s about the limit for a sheet material that will slow gown a human without killing him/her and because the deceleration is independent of initial speed. The protective suit will protect against cuts.
By soft ground I do not mean: bubble wrap, a net, any system containing springs, vegetation, rubber. They are all deadly at high speed.
Let’s say 24 g is survivable. (People have survived brief accelerations of > 100 g in a crash).
The current high diving record is 52 metres.

I’m not sure what the drop height should be, above 99.99% of the atmosphere for sure, but what it there’s no atmosphere?
Start with the worst case – escape velocity.
Mars, 5,030 m/s
Titan, 2,639 m/s
Moon, 2,380 m/s
Pluto, 1,230 m/s
Ceres, 510 m/s
No chance of survival without an atmosphere there.
The escape velocity is sqrt(2*g*r) where g is the local acceleration due to gravity and r is the radius.
Where g is not known, the escape velocity is proportional to the radius times the square root of the density. So using data from Ceres, for a back-of-envelope approximation, the impact velocity in m/s on an asteroid or comet is equal to its radius in km.
Ryugu has a radius of 400 metres, so the impact velocity is 0.4 m/s. Definitely survivable.
Asteroid Mathilde has a radius of 25 km, so the impact velocity is 25 m/s. Hmm.
Atmosphere, consider only terminal velocity. The drag coefficient is about 0.5.

Heating is almost solely adiabatic (ram) heating. That’s calculable from atmospheric temperature, density, and fall speed. Or, for subsonic speeds it is. I’m not sure how to calculate heat at supersonic speeds where “A hot shock wave was created in front of the vehicle, which deflected most of the heat and prevented the orbiter’s surface from directly contacting the peak heat. Therefore reentry heating was largely convective heat transfer between the shock wave and the orbiter’s skin through superheated plasma.”
At low densities, the temperature is greatest (because terminal velocity is huge) but because of low air density this is more survivable than at slightly higher air densities.
Then there’s thermal insulation of the protective suit. see https://en.wikipedia.org/wiki/Space_Shuttle_thermal_protection_system