What is engine power vs propeller thrust relation? Given:

speed 30 knots
engine power 70 hp at 5800 RPM
propeller 3 blades, diameter 14 inch, pitch 17 inch, at 2300 RPM
fluid density 1023 kg/m3

I know that each blade is basically one wing.  Calculating lift is extremely complex; even Navier-Stokes equations will not give an accurate result.
But can I estimate the  thrust this produces, for these values or in general?
Power P, stationary thrust T, propeller swept area A, and air density rho are linked by this expression, derived from first principles and momentum theory:
T^3 = 2 · P^2 · A · rho
That's the maximum power available assuming a 100% prop efficiency.
Things change if the prop is moving forward, as in a flying plane. With the forward speed component, the blades have their angle of attack reduced in proportion to that forward speed. The blades work as wings, and a wing profile has a coefficient of lift that changes with the AoA. Drag does also change with a growing AoA, Hence, for every section of a fixed-pitch prop's blade, there's an optimum L/D at a given combination of rotating and forward speeds that gives the best efficiency. For a fixed angular speed of the prop, there is a given forward airspeed at which the prop works with maximum efficiency, that efficiency –and hence the thrust– dropping asymptotically as the forward speed grows...
Concerning the power delivered by a propeller in forward motion, it's the product of the thrust and speed...