There would be some heating; going from that altitude down to 35 kft (basically, the entire range of the stratosphere) in absence of drag would result in a speed of about 860 m/s or almost 2000 miles/hr. That would exceed the speed of sound at that altitude, so you’d certainly get some compression heating at some point as the air density starts to increase significantly around 75 kft, but that would also cause you to lose speed as you transfer excess momentum to compress the air and eventually you’d come to some equilibrium speed, e.g. “terminal velocity” which would continue to decrease as you go down. The amount of heating from ‘skin friction’, e.g. the attachment and separation of ambient air would be minimal just because the density of the air is so low, and the dynamic viscosity actually drops slightly through the stratosphere. In doing hazard limit calculations from a flight termination or breakup, we generally assume no additional breakup due to heating from altitudes below 300 kft, but then, we’re generally considering solid metallic or high temperature composite components, not human bodies. I suspect the total amount of heat flux you would get would not be enough to offset the fact that an unprotected body would be subjected to very cold equivalent temperature.
The reason spacecraft heat up so much upon reentry is because they are coming from orbit (or for ballistic missiles, very high arcs) and are moving much faster than something falling with no initial velocity, so they have a lot of momentum to shed, virtually all of which is converted into thermal energy in the shock wave during reentry. They therefore require thick shields that protect the reentering spacecraft from both radiative heating and the ionized gases created by such heating.