1. The problem statement, all variables and given/known data Open ended problem really, nothing is given except that I need a thrust of 30 lbf. Similar to dyson fan which entrains and induces air, increasing airflow 15 times. Working around this concept, I'm trying to design a nozzle so I can calculate the ratio of inlet and exit areas. So far I know that for the most efficient nozzle, the exit pressure must equal atmospheric. This is all for subsonic flow. 2. Relevant equations Wasn't exactly sure where to start, so I took Bernoulli's equation (ignoring gz term), substituted the conservation of mass terms, and plugged that into a thrust equation. 3. The attempt at a solution Bernoulli's: Vi^2/2 + Pi/rho = Ve^2 + Patm/rho COM: Ai*Vi = Ae*Ve Thrust: F= mdot*Ve + (Pe-Patm)Ae, Pe=Patm Throw that all together, F = rho *(Ae^2/Ai)*Vi *sqrt(Vi^2 + 2(Pi - Patm)/rho)) Here I have 4 unknowns if I have a constraint that F must equal 30lbf. I could set Ae^2/Ai as a ratio and take it down to 3 unknowns, but that doesn't help much. Any thoughts on how I could nail this down so I have one input and output?