I'm thinking about effect a propeller's pitch has on wing performance, specifically velocity needed for lift to equal weight. I made the diagram below demonstrating what I am curious about. In this example, I have an engine and propeller delivering 150lbs on a static sled on the left. If I cant the angle of the machine upwards 15%, am I correct to assume the changes on the right to the horizontal and vertical thrust components? If so, how do I achieve net increase thrust? Is a 45deg angle the peak power delivery and my horizontal example is a coefficient of the max potential?

My second question: Does the vertical thrust component carry over to the wings? If I increase vertical thrust, do the wings perform as if the aircraft is lighter by a corresponding factor?

Thanks for any clarification you might give.