cfd analysis of an accelerated projectile, speed 0-M3 -- 2

i need support for my study task: a tiny rocket dia 4mm, length 60mm, needs a laminar flow that "sucks" the airflow into the center axis behind the projectile´s tail. the task is 1. to show the "coanda" effect at different velocities (0-M3), and 2. how this effect can be locally disturbed by what forces applied, and 3. how the thrust jet is influenced/squeezed by the orthogonal pressure vector caused by the coanda effect. please only apply if you are a fluid dynamics specialist. so i propose these milestones: milestone1: 50$ create any rocket and fin-form form you want, od 4mm, length 60mm. show the "coanda" effect at different velocities (0-M3), show and measure the vector force pressing perpendicularly inwards, optimize the rocket´s round end in order to reach highest vector force over velocity range. milestone2: 50$ show how this effect can be locally disturbed by what forces applied to the rounded region in order to let laminar flow stall. think of a foil with a rough surface (range 0-50µm of ie bubbles) that you glue to that region. Eliminate as much as possible the “sucking” effect. Show best roughness geometry. milestone3: 50$ create a thrust that propels the rocket to M2.5-3 within ideally 20m. show energy used on 0-100m, acceleration chart and thrust and drag and weight chart. Use any useful powder and metal, that s not important. What I need is a realistic thrust with a realistic cone geometry. milestone4: 50$ show how the thrust jet is influenced/squeezed by the orthogonal pressure vector caused by the coanda effect and released w/o coanda effect. If the rough stall producing foil would be just half around the rocket s end: what would be the turn rate? Optimize the fins to produce highest and lowest turn rate.