I've been writing a computer simulation for a small satellite
launcher, and have discovered a mistake in my code!

The mistake isn't quite relevant to the question I want to ask, but
related.

I've been modelling aerodynamic drag in the lower part of the
atmosphere as constant * airdensity * velocity * velocity.

I realise that the constant will vary according to the design (area,
shape), but I was wondering whether anyone could point me to, or give
me some idea of, the size of the drag forces on something like Scout
or Titan II.

Many thanks,

Nicholas Hill