Consider the Falcon 9.
In emergencies, the launch escape system will fire to separate and propel the crew module away from the rocket.
After the engine shuts down, the payload trunk will separate leaving the crew module to carry on alone.
The crew module, being aerodynamically unstable by design, will quickly flip over so that its heat shield is facing forward.
And this means a big change in the drag coefficient of the crew module.
Before the flipover, the streamlined ogive-like nose will aim into the wind, giving a fairly low drag coefficient. After the flipover, the blunt heat shield will aim into the wind, giving a fairly high drag coefficient.
I know there is no data out there for the drag coefficient, but if it is/were close to other ogive-like vehicles, then roughly what values would you expect? Would 0.3 for nose-forward and 1.5 for heatshield-forward be in the ballpark of reasonable?
I’m ignoring dependencies on speed and altitude at my peril. Just trying to get a baseline expectation for the change on the drag coefficient due to the flipover alone.
Even better, is there data out there for a flipover of an pointy vehicle with a blunt heat shield?
Rough and approximate are fine for my purposes. Think “ballpark” if you don’t have exact numbers.