(For the TL:DR version, scroll down to the bottom of the post.)
It is the position, or opinion of some (such as the writer of this
blog post) that liquid hydrogen/oxygen ('hydrolox') rocket engines are a poor choice for first stages of launch vehicles, because they are 'thrust limited' and/or have a lower engine T/W.
However, there is no intrinsic correlation between thrust and propellant combination. If you had the motivation, resources and time, you could theoretically...